Patent CN111114774B — Rotorless Flying Saucer Powered by Electromagnetic Field (Zhejiang University)
Bibliographic Information
| Field | Details |
|---|---|
| Patent Number | CN111114774B |
| Title | A Rotorless Flying Saucer Powered by an Electromagnetic Field and Its Flight Method |
| Inventors | Meng Zhu (孟濬), Yu Huize (于惠泽) |
| Assignee | Zhejiang University (浙江大学, ZJU) — one of China's top-ranked research universities |
| Filing Date | December 31, 2019 |
| Publication Date | May 8, 2020 (initial); October 22, 2021 (grant) |
| Status | Active — anticipated expiration December 31, 2039 |
| Worldwide Applications | CN 2019, JP 2020, WO 2020 |
| Jurisdiction | China (CN) |
Abstract
The invention discloses a rotorless flying saucer powered by an electromagnetic field and a flying method thereof. The flying saucer includes a control unit, an analysis unit, and an execution unit. The flying saucer execution unit includes a lift module that provides lift for the flying saucer and a horizontal plane power module that provides the flying saucer with forward power in all directions. The lift module generates an ion current through an ion generator, and a changing magnetic field can be generated by passing a changing current to the coil, and the ion current rotates in the changing magnetic field. The horizontal plane power module can generate ion currents in different directions through the evenly distributed ion generator, and provide the flying saucer with power in all directions on the horizontal plane.
Claims (Summary from Patent)
The patent presents multiple claims defining:
Independent Claim 1: A rotorless flying saucer powered by electromagnetic field comprising a control unit, an analysis unit, and an execution unit; wherein the execution unit includes a lift module and a horizontal plane power module; the lift module generates ion current through ion generators and produces changing magnetic field through a coil with changing current; the ion current rotating in the changing magnetic field produces vertical Lorentz force for lift; the horizontal plane power module includes evenly distributed ion generators generating ion currents in selectable directions; and the control unit and analysis unit coordinate to produce commanded flight trajectory.
Additional claims specify:
- Minimum 16 ion generators total (2 vertical for lift, at least 14 horizontal pairs for omnidirectional horizontal thrust)
- Maximum electrode voltage: less than 100 kV
- Electrode spacing: approximately 1 meter
- Target thrust-power ratio: minimum 50 N/kW
- Control architecture with path planning module, judgment module, signal interface, data acquisition, and central processor
Description / Specification
System Architecture: Three-Unit Design
Control Unit (Ground-based or remote):
- Sends flight missions and receives status updates via wireless communication (WiFi, Bluetooth, Zigbee)
- Path planning module generates commanded trajectory
Analysis Unit (Onboard):
- Processes flight instructions and manages system operations
- Sensor suite: gyroscopes, accelerometers, ultrasonic sensors, GPS modules
- Judgment module: assesses current state vs. commanded trajectory
- Signal interface: translates commands to execution unit controls
Execution Unit (Propulsion):
- Lift module: Ion generators above and below electromagnetic coil → vertical Lorentz force
- Horizontal power module: Ion generators distributed around aircraft edge → omnidirectional horizontal thrust
Physics Mechanism: Lorentz Force Propulsion via Ion Current × AC Magnetic Field
The ion generator produces a stream of singly charged ions (proton or air-ion plasma) at controlled current density J, generated by high-voltage electrodes (~15,000 V, up to 100 kV maximum) ionizing air molecules. The coil generates an alternating magnetic field:
B(t) = B₀ sin(ωt)
The Lorentz force on the ion current:
F = J × B = J × B₀ sin(ωt)
For net (non-zero time-averaged) thrust, the ion current must be synchronized with the magnetic field phase. When J and B are in phase, the time-averaged force:
⟨F⟩ = ½JB₀
is non-zero and directed upward (lift module) or horizontally (horizontal power module).
Thrust-Power Ratio Formula
The thrust-to-power ratio:
T/P = (ρĒA) / (jL)
Where:
- ρ = charge density (C/m³)
- Ē = electric field intensity (V/m)
- A = electrode contact area (m²)
- j = current density (A/m²)
- L = electrode separation (m)
Target minimum: 50 N/kW (per patent specification). This is significantly higher than many conventional electric propulsion systems and is the key performance metric the design must achieve to be practical.
Omnidirectional Horizontal Maneuvering
The horizontal power module's omnidirectional capability:
- Ion generators are distributed uniformly around the aircraft's perimeter
- By selectively activating generators at different azimuthal positions, the net horizontal force vector can be directed in any horizontal direction
- No rotation of the craft body is required for directional change
- Differential activation of opposing generators provides turning
This directly addresses the observed UAP characteristic of instantaneous directional change without the craft rotating — the force vector changes while the craft attitude remains constant.
Design Parameters
| Parameter | Specification |
|---|---|
| Total ion generators | Minimum 16 |
| Vertical (lift) generators | 2 |
| Horizontal (thrust) generator pairs | Minimum 14 (7 pairs) |
| Maximum electrode voltage | < 100 kV |
| Electrode spacing | ~1 meter |
| Target thrust-power ratio | ≥ 50 N/kW |
Key Advantages Claimed
- Zero pollutant emission — no combustion products, purely electromagnetic
- Silent operation — no rotating blades, no acoustic signature from propulsion
- Enhanced safety — no rotating components that can injure nearby persons
- Precision control — electronic phase control, no mechanical adjustment required
- Versatility — applicable for delivery, agricultural seeding, surveillance
Practical Applications (per Patent)
- Nighttime package delivery — silent operation avoids disturbing residents
- Precision agricultural seeding — no rotor downwash disturbing crops
Strategic Significance
Filed by Zhejiang University with simultaneous PCT filing (JP 2020, WO 2020), this is an active Chinese academic patent on electromagnetic disc-craft propulsion. Zhejiang University (ZJU) is a key institution in China's military-civil fusion programs; its patents routinely transition to PLA (People's Liberation Army) applications.
The simultaneous PCT extension to Japan and international jurisdictions mirrors the strategic filing patterns seen in:
- Raytheon's 1959 patent US3114517A (US + GB + BE + JP, Track_11)
- Nanjing University CN109573106B (Track_23, simultaneous international)
The strategy of protecting strategically significant aerospace IP in multiple major jurisdictions simultaneously indicates commercial and strategic intent, not merely academic publication.
Technical Classifications
- B64C39/001 — Flying saucers (explicitly classified)
- B64G1/409 — Unconventional spacecraft propulsion systems (implied)
Relationship to Other Patents in This Archive
| Patent | Relationship |
|---|---|
| US3322374A (Track_18) | Foundational MHD J×B principle, 1967 |
| CN111038740A (Track_7) | Chinese spherical EM craft, same generation |
| RU2106287C1 (Track_8) | Russian disc with 16-coil array — similar principle |
| RU2046210C1 (Track_14) | Russian toroidal J×B disc engine |
Citations
- Google Patents: CN111114774B
- Zhejiang University military-civil fusion program
- PCT/CN2020/000001 or equivalent international application (WO 2020)
Patent text compiled from Google Patents. Machine-translated from Chinese; original Chinese text at the above URL.