CN101758925A - Personal automatic aircraft - Google Patents
Personal automatic aircraft Download PDFInfo
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- CN101758925A CN101758925A CN200810187846A CN200810187846A CN101758925A CN 101758925 A CN101758925 A CN 101758925A CN 200810187846 A CN200810187846 A CN 200810187846A CN 200810187846 A CN200810187846 A CN 200810187846A CN 101758925 A CN101758925 A CN 101758925A
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- aircraft
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- personal
- autopilot
- flight
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Abstract
The invention belongs to the aircraft technology field, relates to an aircraft for personal use and provides a personal aircraft which has small volume, is easy to drive, can vertically take off and land and horizontally fly. The main body of the aircraft is a delta-winged structure (1); outer ends of a wing are respectively provided with a ducted fan (3); two engines (2) are arranged at the left side and the right side of the back end of the aircraft; a sensor (4) and an autopilot (5) are arranged. The personal aircraft has the advantages that: the characteristics of a rotary wing aircraft and a fixed wring aircraft are combined, the rotary wing aircraft has the characteristic of vertically taking off and landing and the fixed wing aircraft has the characteristic of high flying efficiency; the autopilot (5) is arranged, automatically taking off and landing is realized, the operation is simple; the ducted fan (3) is selected to control the stability of the aircraft, low speed flying and hovering can be realized. The aircraft can be used in the sport, the civil and military field.
Description
Technical field
The invention belongs to the vehicle technology field, be a kind of aircraft of individual's use.
Background technology
At present aircraft mainly is divided into three kinds of rotor, fixed-wing and flapping wings.The characteristics that rotor craft has vertical lift and hovers, airworthiness and handling are better, but flight efficiency is low.The fixed-wing aircraft is adapted at aerial high-speed flight, and flying speed is very fast, but the take-off venue is required harsh.Flapping wing aircraft still is in the exploratory stage at present, and that is that all right is ripe for technology, can not reach practical purpose.
Summary of the invention
The rotary-wing flight efficient that exists in the prior art is low in order to overcome for technical scheme of the present invention, the fixed-wing aircraft requires harsh shortcoming to the take-off venue, a kind of brand new personal aircraft is proposed, this flying instrument has following advantage: in conjunction with the advantage of rotor and fixed-wing aircraft, both had the characteristics of rotor craft energy vertical takeoff and landing, had the high characteristics of fixed-wing aircraft flight efficient again; Be equipped with autopilot (5), realize automatic landing, easy and simple to handle; Select the steady certainly of duct formula fan (3) controlling aircraft, can realize low-speed operations and hovering.
Technical scheme of the present invention
A kind of personal aircraft, this aircraft provides the power that hovers and fly by the driving engine (2) of rear end, and the thrust of two driving engines (2) can independently be controlled, and the moment that produces by the thrust difference of controlling two driving engines (2) is come the direction of controlling aircraft; Roll and pitching by duct formula fan (3) controlling aircraft on the wing; Gather the information such as attitude, speed, height of aircraft by sensor (4), by the flight of the common controlling aircraft of aviator and autopilot (5).
Said sensor (4) comprises attitude measurement system, altimeter, Pitot meter and ultrasonic range finder.Attitude measurement system is used for measuring at any time the drift angle of aircraft and three axles, three axial acceleration/accels and around three cireular frequency; Altimeter is used to measure the sea level elevation of aircraft; Pitot meter is used to measure the relative velocity of aircraft; Ultrasonic range finder is used to measure aircraft and ground-surface distance.
Said autopilot (5) comprises driving engine (2) controller, duct formula fan (3) controller, flight self-stabilization control system, GPS receiver, radio station and navigation control system.Driving engine (2) controller is controlled the horsepower output of driving engine (2) by electric signal; Duct formula fan (3) controller is controlled the rotating speed of fan by electric signal and is turned to; The information that flight self-stabilization control system is gathered according to sensor (4) is calculated the flicon parameter in real time, by the state of flight of driving engine (2) controller and duct formula fan (3) controller controlling aircraft, realizes the autostable flight of aircraft; The GPS receiver is used to receive the gps data of aircraft current location; Radio station is used for communication contact and control data transmission; Navigation control system is comprehensively determined the heading and the flying height of aircraft according to gps data and the gps data of object point and the control data that radio station receives of current location, realizes the automatic navigation of aircraft.
Beneficial effect of the present invention:
The present invention organically combines rotor and fixed-wing aircraft, has both had the characteristics of rotor craft energy vertical takeoff and landing, has the high characteristics of fixed-wing aircraft flight efficient again; Adopt twin-engined (2) structure, come the direction of controlling aircraft, help optimizing the pneumatic structure of aircraft, make aircraft be easy to control by the thrust that changes two driving engines (2); Be equipped with autopilot (5), realize automatic landing and flight automatically, the easy operation of aircraft has strengthened the safety of flight; By the roll and the pitching of duct formula fan (3) controlling aircraft on the wing, do not influence the speed of aircraft in the control process, improved the efficient of aircraft.
Description of drawings
The present invention has 3 accompanying drawings.
Fig. 1, backplan of the present invention;
The three-view diagram of Fig. 2, structure of the present invention;
Fig. 3, the scheme drawing that takes off of the present invention;
The specific embodiment
As shown in Figure 1, personal aircraft of the present invention mainly is made up of delta wing structure (1), driving engine (2), duct formula fan (3), sensor (4) and autopilot (5).The main body of this aircraft is delta wing structure (1), and respectively there is a delta shaped wing both sides, produces lift when wing is used for horizontal flight; There is bindiny mechanism the below, middle part of structure, is used for aircraft is fixed in aviator's back; In the outer end of wing a duct formula fan (3) is arranged respectively, the rotating speed of duct formula fan (3) and turn to and to be controlled, the roll and the pitching of the comprehensive counter torque controlling aircraft that produces by duct formula fan (3); A driving engine (2) is respectively arranged about the aircraft rear end, driving engine (2) by the rear end provides the power that hovers and fly, the thrust of two driving engines (2) can independently be controlled, and the moment that produces by the thrust difference of controlling two driving engines (2) is come the direction of controlling aircraft; Sensor (4) and autopilot (5) are installed at the middle part of aircraft, are used to gather the information such as attitude, speed, height of aircraft, come the automatic flight of controlling aircraft by autopilot (5); Dead ahead at aircraft is equipped with Pitot meter, is used for the relative velocity of sense aircraft; At the middle part of aircraft a ultrasonic range finder is arranged downwards, when being used for the testing flying vehicle horizontal flight and ground-surface distance; In the back of aircraft a ultrasonic range finder is arranged backward, arrive ground-surface distance when being used to measure the aircraft vertical lift.
Claims (1)
1. a personal aircraft is characterized in that: rotor and fixed-wing aircraft are combined, have the advantage of two kinds of aircraft; Come the direction of controlling aircraft by the thrust that changes two driving engines (2); Roll and pitching by duct formula fan (3) controlling aircraft on the wing; Come the flight of common controlling aircraft by aviator and autopilot (5); Realized taking off automatically and land.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200810187846A CN101758925A (en) | 2008-12-24 | 2008-12-24 | Personal automatic aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200810187846A CN101758925A (en) | 2008-12-24 | 2008-12-24 | Personal automatic aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101758925A true CN101758925A (en) | 2010-06-30 |
Family
ID=42490342
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200810187846A Pending CN101758925A (en) | 2008-12-24 | 2008-12-24 | Personal automatic aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101758925A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104960665A (en) * | 2015-06-29 | 2015-10-07 | 田悦丰 | Aircraft having multiple flight modes |
| CN107813927A (en) * | 2016-09-11 | 2018-03-20 | 郎风 | Dalta wing is coaxially to turning duct aircraft |
| CN109606635A (en) * | 2018-12-29 | 2019-04-12 | 杨春鹏 | Adjustable wing can VTOL delta-winged aircraft |
| US10683098B2 (en) | 2015-06-29 | 2020-06-16 | Yuefeng TIAN | Driving device assembly with multiple drive devices and application thereof |
-
2008
- 2008-12-24 CN CN200810187846A patent/CN101758925A/en active Pending
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104960665A (en) * | 2015-06-29 | 2015-10-07 | 田悦丰 | Aircraft having multiple flight modes |
| US10683098B2 (en) | 2015-06-29 | 2020-06-16 | Yuefeng TIAN | Driving device assembly with multiple drive devices and application thereof |
| CN107813927A (en) * | 2016-09-11 | 2018-03-20 | 郎风 | Dalta wing is coaxially to turning duct aircraft |
| CN109606635A (en) * | 2018-12-29 | 2019-04-12 | 杨春鹏 | Adjustable wing can VTOL delta-winged aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20100630 |