CN202481316U - Aircraft flight vehicle - Google Patents
Aircraft flight vehicle Download PDFInfo
- Publication number
- CN202481316U CN202481316U CN2012200379029U CN201220037902U CN202481316U CN 202481316 U CN202481316 U CN 202481316U CN 2012200379029 U CN2012200379029 U CN 2012200379029U CN 201220037902 U CN201220037902 U CN 201220037902U CN 202481316 U CN202481316 U CN 202481316U
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- CN
- China
- Prior art keywords
- gas cylinder
- control unit
- groove
- housing
- loud
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The utility model discloses an aircraft flight vehicle which comprises a casing and a ring-shaped wing, wherein the casing is provided with a groove matched with the ring-shaped wing, the ring-shaped wing is embedded into the groove and movably connected with the casing, a stator coil is arranged in the groove, a rotor coil is arranged in the ring-shaped wing in a burying mode, and a dynamic device and a control unit are arranged on the bottom of the casing. The dynamic device comprises a flammable ice storing device, a fuel gas cylinder and a regulated directional device. The flammable ice storing device is connected with the fuel gas cylinder through a pipeline. The regulated directional device is arranged on the pipeline. The control unit is connected with the flammable ice storing device. An electric nozzle connected with the control unit is arranged inside the fuel gas cylinder. The aircraft flight vehicle saves energy and protects environment due to the fact that a new energy is adopted as a power source.
Description
Technical field
The utility model relates to a kind of aircraft, belongs to field of aerospace technology.
Background technology
At present; Multinationally developed or developed Dished aircraft, but such aircraft still with fossil fuel as propulsion source, along with the violent minimizing of earth petroleum-based energy; And the exploitation of new forms of energy, it is one of research and development target that new forms of energy are applied on the aerospacecraft.
Also have some course of new aircraft to adopt nuclear power source, accordingly nuclear reactor and related facility need be set, apparatus structure is complicated, and not only cost of manufacture is high, and because the fugitiveness of nuclear, in case leak, with causing the loss that can not estimate.
Based on this, how to research and develop a kind of novel aerospacecraft, as power, reduce pollution with the renewable new forms of energy of the earth to environment.
Summary of the invention
The utility model provides a kind of aerospacecraft that adopts new forms of energy as power, stable performance, safety and environmental protection in order to solve the problem of existing not environmental protection of aerospacecraft propulsion source.
In order to solve the problems of the technologies described above, the utility model adopts following technical scheme to be achieved:
A kind of aviation aircraft comprises the housing and the annular wing, and said housing has the groove that coincide with the annular wing; The said annular wing embeds groove and housing flexibly connects; In groove, be provided with stator coil, in the said annular wing, be embedded with rotor winding, housing bottom is provided with engine installation and control unit; Said engine installation comprises combustible ice memory device, gas cylinder and device for regulating direction; Said combustible ice memory device and gas cylinder are through plumbing connection, and said device for regulating direction is arranged on the pipeline, and said control unit is connected with the combustible ice memory device; It is that gas cylinder, device for regulating direction supply combustible ice that control unit can be controlled the combustible ice memory device, in said gas cylinder, is provided with and control unit bonded assembly EFI mouth.
Further, said engine installation also comprises this gas reservoir of loud, high-pitched sound, and this gas reservoir of said loud, high-pitched sound is connected with gas cylinder.
Preferably, this gas reservoir of said loud, high-pitched sound is 2.
Preferably, in order to make full use of solar electrical energy generation, be provided with the solar power silicon plate at said surface of shell.
Further again, the gas that the back of will burning for ease produces is discharged, and is provided with freeing pipe in said gas cylinder one side.
Compared with prior art, the advantage and the good effect of the utility model are: the aviation aircraft of the utility model adopts new forms of energy as propulsion source, energy-conserving and environment-protective.
After the detailed description in conjunction with advantages the utility model embodiment, other characteristics of the utility model and advantage will become clearer.
Description of drawings
Fig. 1 is a kind of example structure scheme drawing of aerospacecraft that the utility model proposes;
Fig. 2 is the detail view of Fig. 1 middle shell 1 and the annular wing 2 junctions;
Fig. 3 is that a kind of embodiment engine installation of aerospacecraft that the utility model proposes is connected scheme drawing with control unit;
Fig. 4 is a gas cylinder schematic block circuit diagram among Fig. 3.
The specific embodiment
Below in conjunction with accompanying drawing the specific embodiment of the utility model is done explanation in further detail.
Embodiment one, referring to shown in Figure 1, and the aviation aircraft of present embodiment; Comprise the housing 1 and the annular wing 2,, be the detail view of housing 1 with the annular wing 2 junctions referring to shown in Figure 2; Said housing 1 has the groove 3 that matches with the annular wing 2, and the said annular wing 2 embeds groove 3, flexibly connects with housing 1; In groove, be provided with stator coil 4, in the said annular wing 2, be embedded with rotor winding 5, when stator coil 4 is switched on rotor winding 5; The annular wing 2 can be along high speed rotating in the groove 3 under electromagnetic field effect, and housing 1 bottom is provided with engine installation and control unit 10, is used to aviation aircraft power is provided; Referring to shown in Figure 3, be above-mentioned two-part connection scheme drawing, said engine installation comprises combustible ice memory device 6, gas cylinder 7 and device for regulating direction 8; Said combustible ice memory device 6 is connected through pipeline 9 with gas cylinder 7, and said device for regulating direction 8 is arranged on the pipeline 9, and said control unit 10 is connected with combustible ice memory device 6; With control combustible ice memory device 6 is that gas cylinder 7 supplies combustible ice, in said gas cylinder, is provided with and control unit bonded assembly EFI mouth 11, is used for ignited fuel.
For the economic combustion combustible ice, improve combustion efficiency, said engine installation also comprises this gas reservoir 12 of loud, high-pitched sound; This gas reservoir 12 of said loud, high-pitched sound is connected with gas cylinder 7; These gas reservoir 12 internal memories of loud, high-pitched sound contain this gas of loud, high-pitched sound, and it provides loud, high-pitched sound this gas to gas cylinder 7, burning in gas cylinder 7.This gas reservoir 12 of said loud, high-pitched sound preferably is provided with 2, is separately positioned on the both sides of gas cylinder 7.
In order to make full use of solar electrical energy generation, preferably be provided with the solar power silicon plate on said housing 1 surface, being used for conversion of solar energy is that electric energy is the power supply of aircraft internal unit.
The gas that will produce after will burning is for ease discharged, and is provided with freeing pipe 13 in said gas cylinder 7 one sides.Referring to shown in Figure 4, the schematic block circuit diagram for control gas cylinder 7 comprises magnetic board, filter, inductor, fuse; Said magnetic board is carried in gas cylinder 7 two ends; For it power supply is provided by the solar power silicon plate, filter is used to prevent the electromagnetic signal of magnetic board to leak, and inductor can be responded to the power of electromagnetic field in the gas cylinder; Fuse is used for control and crosses when strong the control circuit interruption when magnetic signal.The similar canopy of the heavens of magnetic board static charge is assembled it down, the input air conditioning quantity, and this gas of loud, high-pitched sound that the input of gas cylinder both sides is filtered, the EFI mouth is lighted this gas of loud, high-pitched sound; Blast produces the enormous impact energy, discharges with freeing pipe 13, becomes propulsive effort; But qualitative analysis, quantitative Analysis, blast produces blue light, guides out through corresponding pipeline; The output of irradiation radioistotope becomes laser can be utilized peacefully, and to the radioistotope shielding protection, laser disappears.
Certainly; Above-mentioned explanation is not to be the restriction to the utility model; The utility model also be not limited in above-mentioned for example, variation, remodeling, interpolation or replacement that those skilled in the art are made in the essential scope of the utility model also should belong to the protection domain of the utility model.
Claims (5)
1. aviation aircraft is characterized in that: comprise the housing and the annular wing, the groove that said housing has and the annular wing coincide; The said annular wing embeds groove and housing flexibly connects, and in groove, is provided with stator coil, in the said annular wing, is embedded with rotor winding; Housing bottom is provided with engine installation and control unit; Said engine installation comprises combustible ice memory device, gas cylinder and device for regulating direction, and said combustible ice memory device and gas cylinder are through plumbing connection, and said device for regulating direction is arranged on the pipeline; Said control unit is connected with the combustible ice memory device, in said gas cylinder, is provided with and control unit bonded assembly EFI mouth.
2. aviation aircraft according to claim 1 is characterized in that: said engine installation also comprises this gas reservoir of loud, high-pitched sound, and this gas reservoir of said loud, high-pitched sound is connected with gas cylinder.
3. aviation aircraft according to claim 2 is characterized in that: this gas reservoir of said loud, high-pitched sound is 2.
4. aviation aircraft according to claim 1 is characterized in that: be provided with the solar power silicon plate at said surface of shell.
5. according to the described aviation aircraft of each claim of claim 1-4, it is characterized in that: be provided with freeing pipe in said gas cylinder one side.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012200379029U CN202481316U (en) | 2012-02-07 | 2012-02-07 | Aircraft flight vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012200379029U CN202481316U (en) | 2012-02-07 | 2012-02-07 | Aircraft flight vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202481316U true CN202481316U (en) | 2012-10-10 |
Family
ID=46955762
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012200379029U Expired - Fee Related CN202481316U (en) | 2012-02-07 | 2012-02-07 | Aircraft flight vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202481316U (en) |
-
2012
- 2012-02-07 CN CN2012200379029U patent/CN202481316U/en not_active Expired - Fee Related
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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: 20121010 Termination date: 20140207 |