CN204988031U - Platform is launched in air to electronic aircraft of external power source - Google Patents
Platform is launched in air to electronic aircraft of external power source Download PDFInfo
- Publication number
- CN204988031U CN204988031U CN201520726741.8U CN201520726741U CN204988031U CN 204988031 U CN204988031 U CN 204988031U CN 201520726741 U CN201520726741 U CN 201520726741U CN 204988031 U CN204988031 U CN 204988031U
- Authority
- CN
- China
- Prior art keywords
- power source
- external power
- electric aircraft
- electromagnetic
- platform
- 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
Links
Landscapes
- Toys (AREA)
Abstract
Platform is launched in air to electronic aircraft of external power source uses the aerial platform transmission method of the electronic aircraft of external power source, and characterized by includes electronic aircraft, external power source, electromagnetic propulsion ware assembly and ground -control center, and electronic aircraft includes rotor craft, adjustable wing aircraft and stationary vane aircraft, the electromagnetic propulsion ware turns into the electric energy kinetic energy of load, external power source passes through aerial electromagnetic emission platform of power transmission line supply and electromagnetic propulsion ware. Platform is launched in air to electronic aircraft of external power source, characterized by include electronic aircraft, external power source and ground -control center, and external power source passes through the aerial rocket launching platform of the power transmission line supply electronic aircraft of external power source. The utility model discloses the use can realize promoting the rocket to thousands of BRAT degree and giving its huge kinetic energy by palingenetic electric power.
Description
Technical field
The utility model relates to external power source Electric aircraft Air Launched Platform.
Background technology
Existingly a kind ofly utilize large aircraft vehicle rocket with the technical scheme of alternative mother missile, but the runway that large aircraft needs is long, also almost cannot aloft for rocket provides the acceleration of many times.
Summary of the invention
The purpose of this utility model to provide external power source Electric aircraft Air Launched Platform.
External power source Electric aircraft Air Launched Platform of the present utility model, can do like this: manufacture an external power source Electric aircraft airborne electromagnetic flat pad, comprise Electric aircraft, external power source, electromagnetic propeller assembly, power capacitor, external power source Electric aircraft airborne electromagnetic flat pad computer control system, power transmission line, safety parachute and ground control centre, Electric aircraft comprises rotor craft, adjustable wing aircraft and Fixed Wing AirVehicle; The load that electromagnetic propeller assembly comprises electromagnetic propeller and is in transmission connection with electromagnetic propeller electromagnetic coupled; Electric energy conversion is the kinetic energy of load by electromagnetic propeller; Electromagnetic propeller load includes but not limited to rocket and gliding flight thing; The load of rocket includes but not limited to artificial satellite; Power capacitor stores electric power and is used for electromagnetic propeller; The placement location of external power source comprises on the vehicle on ground; External power source is by power transmission line supply external power source Electric aircraft airborne electromagnetic flat pad and electromagnetic propeller; The power supply electric line of powering for Electric aircraft and the power transmission line of powering for electromagnetic propeller assembly separately use or merge and use; Rocket comprises the rocket of more than one-level;
When external power source Electric aircraft airborne electromagnetic flat pad uses, the first step: make Electric aircraft start external power source Electric aircraft airborne electromagnetic flat pad and go up to the air and accelerate, meeting the requirements of height and emission rate, being included in lift-off to making emission rate reach 10 to 200 meter per seconds during 1 to 20 kilometer range height; Second step: utilize electromagnetic propeller load and rocket to be accelerated to 20 to 300 meter per seconds or higher, and rocket is separated with external power source Electric aircraft airborne electromagnetic flat pad; Then rocket lighted in good time start the next stage fly; External power source Electric aircraft airborne electromagnetic flat pad is then finished the work and is returned, or enter the 3rd step: electromagnetic propeller reloads load, and to power capacitor charging until external power source Electric aircraft airborne electromagnetic flat pad recovers to meet the requirements of height and emission rate, recycle above-mentioned second step to implement again to launch, or;
Omit electromagnetic propeller and form an external power source Electric aircraft Air Launched Platform, comprise Electric aircraft, external power source, aerial rocket launch platform computer control system, power transmission line, safety parachute and ground control centre, Electric aircraft comprises rotor craft, adjustable wing aircraft and Fixed Wing AirVehicle; The load of Electric aircraft includes but not limited to rocket and gliding flight thing; The load of rocket includes but not limited to artificial satellite; The placement location of external power source comprises on the vehicle on ground; External power source is by the aerial rocket launch platform of power transmission line supply; Rocket comprises the rocket of more than one-level;
When external power source Electric aircraft Air Launched Platform uses, Schilling Electric aircraft starts external power source Electric aircraft Air Launched Platform and goes up to the air and accelerate, meeting the requirements of height and emission rate, being included in lift-off to making emission rate reach 10 to 200 meter per seconds during 1 to 20 kilometer range height; Then, after making rocket direct-fire or rocket being separated with aerial rocket launch platform, row is lighted a fire again.
One of the utility model technical scheme realizing its object: manufacture an external power source Electric aircraft airborne electromagnetic flat pad, comprise Electric aircraft, external power source, electromagnetic propeller assembly, power capacitor, external power source Electric aircraft airborne electromagnetic flat pad computer control system, power transmission line, safety parachute and ground control centre, Electric aircraft comprises rotor craft, adjustable wing aircraft and Fixed Wing AirVehicle; The load that electromagnetic propeller assembly comprises electromagnetic propeller and is in transmission connection with electromagnetic propeller electromagnetic coupled; Electric energy conversion is the kinetic energy of load by electromagnetic propeller; Electromagnetic propeller load includes but not limited to rocket and gliding flight thing; The load of rocket includes but not limited to artificial satellite; Power capacitor stores electric power and is used for electromagnetic propeller; The placement location of external power source comprises on the vehicle on ground; External power source is by power transmission line supply external power source Electric aircraft airborne electromagnetic flat pad and electromagnetic propeller.External power source Electric aircraft airborne electromagnetic flat pad computer control system is connected with ground control centre signal and accepts the control of ground control centre.Safety parachute uses when being used for something unexpected happened.
Electric aircraft can also be made to be the above rotor craft of an axle.
Electric aircraft can also be made to be the above rotor craft of diaxon, between each rotor craft and external power source Electric aircraft airborne electromagnetic flat pad, all to adopt the pitch drive that flies to be in transmission connection; Flight pitch drive is electrically connected by interface circuit and external power source Electric aircraft airborne electromagnetic flat pad computer control system main frame, and the state of flight pitch drive changes according to the change of external power source Electric aircraft airborne electromagnetic flat pad computer control system Host Status.
Can also adopt two electromagnetic propeller propulsion coils, one is electrically connected with external power source; One is electrically connected with onboard electric capacitor.
The utility model realizes the technical scheme two of its object: manufacture an external power source Electric aircraft Air Launched Platform, comprise Electric aircraft, external power source, external power source Electric aircraft Air Launched Platform computer control system, power transmission line, safety parachute and ground control centre, Electric aircraft comprises rotor craft, adjustable wing aircraft and Fixed Wing AirVehicle; The load of Electric aircraft includes but not limited to rocket and gliding flight thing; The load of rocket includes but not limited to artificial satellite; The placement location of external power source comprises on the vehicle on ground; External power source is by the aerial rocket launch platform of power transmission line supply; Rocket comprises the rocket of more than one-level; Safety parachute uses when being used for something unexpected happened.
Electric aircraft can also be made to be the above rotor craft of an axle.
Electric aircraft can also be made to be the above rotor craft of diaxon, between each rotor craft and external power source Electric aircraft Air Launched Platform, all to adopt the pitch drive that flies to be in transmission connection; Flight pitch drive is electrically connected by interface circuit and external power source Electric aircraft Air Launched Platform computer control system main frame, and the state of flight pitch drive changes according to the change of external power source Electric aircraft Air Launched Platform computer control system Host Status.
Beneficial effect: the utility model external power source Electric aircraft aerial platform launching technique and the ambient influnence of equipment to launch site is little, use the electric power that can regenerate meet sustainable development theory, operate without the need to large airport; All adopt a revolute pair mechanism to be connected between each rotor craft with external power source Electric aircraft airborne electromagnetic flat pad, the requirement that direction of propulsion adapts to take off on level land and high inclination-angle climbs can be changed at any time; Adopt two electromagnetic propeller propulsion coils to be electrically connected with external power source and onboard electric capacitor respectively, the electric energy that can the make full use of power capacitor voltage comprised when power capacitor only has during rated voltage 80% also can make the electromagnetic propeller coil be connected with external power source work under rated voltage.
Accompanying drawing explanation
Fig. 1 is the fundamental diagram of two external power source Electric aircraft airborne electromagnetic flat pads.The external power source Electric aircraft airborne electromagnetic flat pad interlude on the left side is enlarged as illustrated with the dotted box; The external power source Electric aircraft airborne electromagnetic flat pad on the right side is directly perceived.
Fig. 2 is the fundamental diagram of an external power source Electric aircraft Air Launched Platform.
In figure, 1. external power source Electric aircraft airborne electromagnetic flat pad; 2. external power source; 3. power transmission line; 4. ground control centre; 5. rotor craft; 6. electromagnetic propeller; 7. load; 8. vehicle; 9. fly pitch drive; 10. automatic lock; 11. external power source Electric aircraft Air Launched Platforms; 12. rockets; 16. Compressed Gas catapult-launching gears.
Detailed description of the invention
Fig. 1 provides embodiment 1.
Embodiment 1, manufacture an external power source Electric aircraft airborne electromagnetic flat pad 1, comprise Electric aircraft, external power source 2, electromagnetic propeller assembly, power capacitor, external power source Electric aircraft airborne electromagnetic flat pad computer control system, power transmission line 3, safety parachute and ground control centre 4, Electric aircraft comprises the rotor craft array be made up of several rotor crafts 5; The load 7 that electromagnetic propeller assembly comprises electromagnetic propeller 6 and is in transmission connection with electromagnetic propeller 6 electromagnetic coupled; External power source 2 is placed on surface car 8; External power source 2 supplies external power source Electric aircraft airborne electromagnetic flat pad 1 by power transmission line 3.External power source Electric aircraft airborne electromagnetic flat pad computer control system is connected with ground control centre 4 signal and accepts the control of ground control centre 4.The pitch drive 9 that flies all is adopted to be in transmission connection between each rotor craft 5 and external power source Electric aircraft airborne electromagnetic flat pad 1; Flight pitch drive 9 is electrically connected by interface circuit and external power source Electric aircraft airborne electromagnetic flat pad computer control system main frame, and the state of flight pitch drive 9 changes according to the change of external power source Electric aircraft airborne electromagnetic flat pad computer control system Host Status.
Containing an automatic lock 10 between electromagnetic propeller 6 and load 7, load 7 be locked on electromagnetic propeller 6, until moment before launching, automatic lock 10 is just opened.About the content of automatic lock can with reference to prior art.
When external power source Electric aircraft airborne electromagnetic flat pad 1 uses, the first step: make each rotor craft 5 start external power source Electric aircraft airborne electromagnetic flat pad 1 and go up to the air and accelerate, meeting the requirements of height and emission rate, being included in lift-off to making emission rate reach 10 to 200 meter per seconds during 1 to 20 kilometer range height; Second step: utilize electromagnetic propeller load and rocket to be accelerated to 20 to 300 meter per seconds or higher, and rocket is separated with external power source Electric aircraft airborne electromagnetic flat pad 1; Then rocket lighted in good time start the next stage fly;
External power source Electric aircraft airborne electromagnetic flat pad 1 in Fig. 1 is vertical state, in fact, can be in any other state.
Fig. 2 provides embodiment 2.
Embodiment 2, manufactures an external power source Electric aircraft Air Launched Platform 11, comprise Electric aircraft, external power source 2, external power source Electric aircraft Air Launched Platform computer control system, power transmission line 3, safety parachute and and ground control centre; External power source 2 supplies external power source Electric aircraft Air Launched Platform 11 by power transmission line 3.Electric aircraft comprises the rotor craft array be made up of several rotor crafts 5; The pitch drive 9 that flies all is adopted to be in transmission connection between rotor craft 5 and external power source Electric aircraft Air Launched Platform 11; Flight pitch drive 9 is electrically connected by interface circuit and external power source Electric aircraft Air Launched Platform computer control system main frame, and the state of flight pitch drive 9 changes according to the change of external power source Electric aircraft Air Launched Platform computer control system Host Status.
Rocket 12 as load 7 is arranged on above external power source Electric aircraft Air Launched Platform 11, and the afterbody of rocket 12 is Compressed Gas catapult-launching gears 16.
When external power source Electric aircraft Air Launched Platform 11 uses, the each rotor craft 5 of Schilling starts external power source Electric aircraft Air Launched Platform 11 and goes up to the air and accelerate, meeting the requirements of height and emission rate, being included in lift-off to making emission rate reach 10 to 200 meter per seconds during 1 to 20 kilometer range height; Then, start Compressed Gas catapult-launching gear 16 rocket 12 is penetrated and makes rocket 12 direct-fire.
Rocket 12 not necessarily will be arranged on the top of external power source Electric aircraft Air Launched Platform 11; Compressed Gas catapult-launching gear 16 also not necessarily will be arranged on the afterbody of rocket 12.Compressed Gas catapult-launching gear 16 also can.The related content of Compressed Gas catapult-launching gear can with reference to prior art.
Claims (6)
1. external power source Electric aircraft airborne electromagnetic flat pad, it is characterized in that comprising Electric aircraft, external power source, electromagnetic propeller assembly, power capacitor, external power source Electric aircraft airborne electromagnetic flat pad computer control system, power transmission line, safety parachute and ground control centre, Electric aircraft comprises rotor craft, adjustable wing aircraft and Fixed Wing AirVehicle; The load that electromagnetic propeller assembly comprises electromagnetic propeller and is in transmission connection with electromagnetic propeller electromagnetic coupled; Electric energy conversion is the kinetic energy of load by electromagnetic propeller; Electromagnetic propeller load includes but not limited to rocket and gliding flight thing; The load of rocket includes but not limited to artificial satellite; Power capacitor stores electric power and is used for electromagnetic propeller; The placement location of external power source comprises on the vehicle on ground; External power source is by power transmission line supply external power source Electric aircraft airborne electromagnetic flat pad and electromagnetic propeller.
2., according to external power source Electric aircraft airborne electromagnetic flat pad according to claim 1, it is characterized in that Electric aircraft is the above rotor craft of an axle.
3. according to external power source Electric aircraft airborne electromagnetic flat pad according to claim 1, it is characterized in that Electric aircraft is the above rotor craft of diaxon, between each rotor craft and external power source Electric aircraft airborne electromagnetic flat pad, all adopt the pitch drive that flies to be in transmission connection; Flight pitch drive is electrically connected by interface circuit and external power source Electric aircraft airborne electromagnetic flat pad computer control system main frame, and the state of flight pitch drive changes according to the change of external power source Electric aircraft airborne electromagnetic flat pad computer control system Host Status.
4. external power source Electric aircraft Air Launched Platform, it is characterized in that comprising Electric aircraft, external power source, aerial rocket launch platform computer control system, power transmission line, safety parachute and ground control centre, Electric aircraft comprises rotor craft, adjustable wing aircraft and Fixed Wing AirVehicle; The load of Electric aircraft includes but not limited to rocket and gliding flight thing; The load of rocket includes but not limited to artificial satellite; The placement location of external power source comprises on the vehicle on ground; External power source is by the aerial rocket launch platform of power transmission line supply.
5., according to external power source Electric aircraft Air Launched Platform according to claim 4, it is characterized in that Electric aircraft is the above rotor craft of an axle.
6. according to external power source Electric aircraft Air Launched Platform according to claim 4, it is characterized in that Electric aircraft is the above rotor craft of diaxon, between each rotor craft and external power source Electric aircraft Air Launched Platform, all adopt the pitch drive that flies to be in transmission connection; Flight pitch drive is electrically connected by interface circuit and external power source Electric aircraft Air Launched Platform computer control system main frame, and the state of flight pitch drive changes according to the change of external power source Electric aircraft Air Launched Platform computer control system Host Status.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520726741.8U CN204988031U (en) | 2015-09-18 | 2015-09-18 | Platform is launched in air to electronic aircraft of external power source |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520726741.8U CN204988031U (en) | 2015-09-18 | 2015-09-18 | Platform is launched in air to electronic aircraft of external power source |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204988031U true CN204988031U (en) | 2016-01-20 |
Family
ID=55122391
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520726741.8U Expired - Fee Related CN204988031U (en) | 2015-09-18 | 2015-09-18 | Platform is launched in air to electronic aircraft of external power source |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204988031U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110174025A (en) * | 2018-02-20 | 2019-08-27 | 南昌市周静新能源有限公司 | A kind of wind and solar integrated new energy guided missile vertical air flat pad |
| CN111891413A (en) * | 2020-06-05 | 2020-11-06 | 宋延军 | Auxiliary system for assisting launching and recovery of aircraft and launching and recovery method |
-
2015
- 2015-09-18 CN CN201520726741.8U patent/CN204988031U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110174025A (en) * | 2018-02-20 | 2019-08-27 | 南昌市周静新能源有限公司 | A kind of wind and solar integrated new energy guided missile vertical air flat pad |
| CN111891413A (en) * | 2020-06-05 | 2020-11-06 | 宋延军 | Auxiliary system for assisting launching and recovery of aircraft and launching and recovery method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| AU2014240295B2 (en) | Short takeoff and landing aircraft | |
| CN105173073A (en) | Composite lift force type unmanned aerial vehicle realizing vertical take-off and landing | |
| CN103101621B (en) | Parafoil aircraft applicable to cylindrical space loading | |
| CN104843181A (en) | Petrol-electric hybrid power fixed wing vertical take-off and landing unmanned plane system | |
| JP2019094051A (en) | Systems and methods for powering electric aerial vehicle | |
| CN102520727B (en) | Reconnaissance system with unmanned plane | |
| CN104960657A (en) | Combined-separate stratospheric aircraft system scheme | |
| CN204988031U (en) | Platform is launched in air to electronic aircraft of external power source | |
| CN105173106A (en) | External power source electric aircraft aerial platform launching method and device | |
| CN103224031A (en) | Landing device of fixed-wing aircraft | |
| CN106628251A (en) | Combined spacecraft and orbiter launching and recycling method | |
| CN202453736U (en) | Unmanned aerial vehicle reconnaissance system | |
| CN104943866A (en) | Airborne training launching device | |
| RU147731U1 (en) | AIRCRAFT | |
| CN101683899A (en) | Launching method of spacecraft | |
| CN105015789A (en) | Potential-energy runway | |
| CN104290916A (en) | Novel electromagnetic take-off/landing runway and air cushion intangible boosting runway of carrier-borne aircraft | |
| CN203958623U (en) | The tail gas balanced system of depopulated helicopter | |
| CN206394895U (en) | Oil electric mixed dynamic rotor manned aircraft | |
| RU2353546C2 (en) | Mobile aircraft rocket-and-space system | |
| CN104044743A (en) | Tail gas balance system of unmanned helicopter | |
| CN202289469U (en) | Remote control toy early warning plane model | |
| RU138371U1 (en) | UNMANNED AERIAL VEHICLE | |
| Begin | The Northrop flying wing prototypes | |
| CN202315308U (en) | Remote control toy fighter plane model |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160120 Termination date: 20170918 |