CN205302005U - Automatic flight of model aeroplane and model ship is with seeking track navigation - Google Patents
Automatic flight of model aeroplane and model ship is with seeking track navigation Download PDFInfo
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- CN205302005U CN205302005U CN201620044074.XU CN201620044074U CN205302005U CN 205302005 U CN205302005 U CN 205302005U CN 201620044074 U CN201620044074 U CN 201620044074U CN 205302005 U CN205302005 U CN 205302005U
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Abstract
The utility model relates to a navigation, especially an automatic flight of model aeroplane and model ship is with seeking track navigation, including installing automatic flight control system, beidou navigation system, inertial navigation system and the solar energy signaling apparatus on model aeroplane and model ship, beidou navigation system connects automatic flight control system, inertial navigation system connects automatic flight control system, automatic flight control system cooperation beidou navigation system and inertial navigation system are equipped with the switching module, the solar energy signaling apparatus includes solar panel, battery charging outfit, lithium cell and location signal transmitter, battery charging outfit, lithium cell and the encapsulation of location signal transmitter through increasing the big dipper and inertial navigation system, have increased navigation's robustness in same hard metal box to reduced the interrupt of navigation, through the solar energy signaling apparatus of increase adoption solar energy as signal receiving and dispatching power, even accidents such as emergence forced landings, control center also can seek the track according to the signal.
Description
Technical field
This utility model relates to a kind of navigation system, and especially a kind of model plane fly automatically with seeking track navigation system.
Background technology
In recent years, the research and development heat of depopulated helicopter has been risen in various countries, and the depopulated helicopter of new research and development competitively occurs in each continent, and at military affairs, emergency response, monitor, take photo by plane and play the part of important function in precision agricultural management etc. Many rotor wing unmanned aerial vehicles, constructing fairly simple, price is also cheaper, and most important is that it does not need emission system, can also VTOL, to environment no requirement (NR) of taking off, advantage maximum compared with fixed-wing is able to aloft freely hover, and flight motility is quite superb, available various speed, flying in the air route of various flight profile, mission profiles, thus than fixed-wing unmanned plane in the difficult task environment such as investigation, rescue, has more application advantage. Many rotor wing unmanned aerial vehicles controller one core calculations unit of many employings in the market, when unmanned plane sensor unit runs into very strong signal disturbing or GPS navigation sensor signal is lost suddenly, core calculations unit is sent out and unstability or deadlock phenomenon can be occurred, operator cannot switch to manual offline mode from automatic offline mode, cause aircraft bombing and fly to lose, causing potential safety hazard.
Study in the industry, such as Chinese patent discloses a kind of many rotor wing unmanned aerial vehicles automatic flight control system, application number: 201420608709.5, the applying date: 2014-10-21, computing unit, full manual control unit, wireless signal transmitting unit and electric-motor drive unit is controlled including flight, flight controls computing unit outfan and connects full manual control unit input, and full manual control unit outfan connects the input of electric-motor drive unit; Flight controls computing unit and is made up of flight attitude derivation device, attitude controller, flight speed detection correcting unit, speed control, flight position detection correction unit, flight position controller, GPS navigation sensor, inertia measurement sensor and baroceptor;Full manual control unit is made up of three-axis gyroscope sensor and angular rate control unit; Wireless signal transmitting unit is received unit by ground station signals Transmit-Receive Unit, remote controller signal and constitutes.
The deficiency of technique scheme is in that: when aircraft is had no progeny automatically in-flight, employing is manual flies, but in practical situation, once after the gps signal loss that flight is used automatically, remote signal is hardly possible smooth and easy transmission also, additionally after gps signal is lost, operator are difficult to judge that various terrain data is to realize the flight of unmanned plane or model plane simply by virtue of naked eyes.
Summary of the invention
For the deficiencies in the prior art, this utility model provides the model plane that a kind of incomplete dependence gps signal flies automatically to seek track navigation system.
The technical solution of the utility model is:
A kind of model plane fly with seeking track navigation system automatically, it is characterized in that: include the automatic flight control system, triones navigation system, inertial navigation system and the solar energy signal indicator that are arranged on model plane, described automatic flight control system includes flight and controls computing unit, full manual control unit, wireless signal transmitting unit and electric-motor drive unit, flight controls computing unit outfan and connects full manual control unit input, and full manual control unit outfan connects the input of electric-motor drive unit; Flight controls computing unit and is made up of flight attitude derivation device, attitude controller, flight speed detection correcting unit, speed control, flight position detection correction unit, flight position controller, GPS navigation sensor, inertia measurement sensor and baroceptor; Full manual control unit is made up of three-axis gyroscope sensor and angular rate control unit; Wireless signal transmitting unit is received unit by ground station signals Transmit-Receive Unit, remote controller signal and constitutes;
Described triones navigation system connects automatic flight control system, described inertial navigation system connects automatic flight control system, described automatic flight control system coordinates triones navigation system and inertial navigation system to be provided with handover module, after gps signal is lost, navigation feature is switched to triones navigation system by flight system, when after GPS and the Big Dipper all lossing signals, navigation feature is switched to inertial navigation system by flight system, handover module adopts the handoff technique that smart mobile phone navigation adopts, and does not repeat herein;
Described solar energy signal indicator includes solar panels, charger, lithium battery and framing signal emitter, described solar panels embed model plane end face, described charger, lithium battery and framing signal emitter package are in same hard metal box, described solar panels are electrically connected charger, described charger is electrically connected lithium battery, and described lithium battery is electrically connected framing signal emitter.
Further, described inertial navigation system is provided with gyroscope, accelerometer and timing correcting device, and described gyroscope adopts the one in electrostatic gyroscope, laser gyro, optical fibre gyro, micromechanical gyro.
Further, described framing signal emitter adopts the discontinuous emitter of 37.5 KHz, and its effect is similar to black box, it is simple to reseaching staff seeks track.
Further, described ground station signals Transmit-Receive Unit be provided with coordinate framing signal emitter receptor, its effect be easy for the dropouts such as GPS after seek track.
The beneficial effects of the utility model are: this utility model simple in construction, by increasing the Big Dipper and inertial navigation system, add the robustness of navigation system, thus decreasing the interruption of navigation, by increasing the solar energy signal indicator adopting solar energy as signal transmitting and receiving power, even if occurring to compel degradation accident, track also can be sought according to signal by control centre, also can provide in properly functioning and seek track data.
Accompanying drawing explanation
Fig. 1 is this utility model structural representation.
In figure, 1, automatic flight control system; 2, triones navigation system; 3, inertial navigation system; 4, solar energy signal indicator; 11, handover module; 12, remote controller signal receives unit; 13, ground station signals Transmit-Receive Unit.
Detailed description of the invention
Below in conjunction with accompanying drawing, detailed description of the invention of the present utility model is described further:
As shown in Figure 1, a kind of model plane fly with seeking track navigation system automatically, it is characterized in that: include the automatic flight control system 1, triones navigation system 2, inertial navigation system 3 and the solar energy signal indicator 4 that are arranged on model plane, described automatic flight control system 1 includes flight and controls computing unit, full manual control unit, wireless signal transmitting unit and electric-motor drive unit, flight controls computing unit outfan and connects full manual control unit input, and full manual control unit outfan connects the input of electric-motor drive unit; Flight controls computing unit and is made up of flight attitude derivation device, attitude controller, flight speed detection correcting unit, speed control, flight position detection correction unit, flight position controller, GPS navigation sensor, inertia measurement sensor and baroceptor; Full manual control unit is made up of three-axis gyroscope sensor and angular rate control unit; Wireless signal transmitting unit is received unit 12 by ground station signals Transmit-Receive Unit 13, remote controller signal and constitutes;
Described triones navigation system 2 connects automatic flight control system 1, described inertial navigation system 3 connects automatic flight control system 1, described automatic flight control system 1 coordinates triones navigation system 2 and inertial navigation system 3 to be provided with handover module 11, after gps signal is lost, navigation feature is switched to triones navigation system by flight system, when after GPS and the Big Dipper all lossing signals, navigation feature is switched to inertial navigation system by flight system, handover module adopts the handoff technique that smart mobile phone navigation adopts, and does not repeat herein;
Described solar energy signal indicator 4 includes solar panels, charger, lithium battery and framing signal emitter, described solar panels embed model plane end face, described charger, lithium battery and framing signal emitter package are in same hard metal box, described solar panels are electrically connected charger, described charger is electrically connected lithium battery, and described lithium battery is electrically connected framing signal emitter.
Further, described inertial navigation system 3 is provided with gyroscope, accelerometer and timing correcting device, and described gyroscope adopts the one in electrostatic gyroscope, laser gyro, optical fibre gyro, micromechanical gyro.
Further, described framing signal emitter adopts the discontinuous emitter of 37.5 KHz, and its effect is similar to black box, it is simple to reseaching staff seeks track.
Further, described ground station signals Transmit-Receive Unit 13 be provided with coordinate framing signal emitter receptor, its effect be easy for the dropouts such as GPS after seek track.
Described in above-described embodiment and description is that principle of the present utility model and most preferred embodiment are described; under the premise without departing from this utility model spirit and scope; this utility model also has various changes and modifications, and these changes and improvements both fall within the scope of claimed this utility model.
Claims (4)
1. model plane fly with seeking track navigation system automatically, it is characterized in that: include the automatic flight control system, triones navigation system, inertial navigation system and the solar energy signal indicator that are arranged on model plane, described automatic flight control system includes flight and controls computing unit, full manual control unit, wireless signal transmitting unit and electric-motor drive unit, flight controls computing unit outfan and connects full manual control unit input, and full manual control unit outfan connects the input of electric-motor drive unit;Flight controls computing unit and is made up of flight attitude derivation device, attitude controller, flight speed detection correcting unit, speed control, flight position detection correction unit, flight position controller, GPS navigation sensor, inertia measurement sensor and baroceptor; Full manual control unit is made up of three-axis gyroscope sensor and angular rate control unit; Wireless signal transmitting unit is received unit by ground station signals Transmit-Receive Unit, remote controller signal and constitutes;
Described triones navigation system connects automatic flight control system, and described inertial navigation system connects automatic flight control system, and described automatic flight control system coordinates triones navigation system and inertial navigation system to be provided with handover module;
Described solar energy signal indicator includes solar panels, charger, lithium battery and framing signal emitter, described solar panels embed model plane end face, described charger, lithium battery and framing signal emitter package are in same hard metal box, described solar panels are electrically connected charger, described charger is electrically connected lithium battery, and described lithium battery is electrically connected framing signal emitter.
2. model plane according to claim 1 fly with seeking track navigation system automatically, it is characterized in that: described inertial navigation system is provided with gyroscope, accelerometer and timing correcting device, and described gyroscope adopts the one in electrostatic gyroscope, laser gyro, optical fibre gyro, micromechanical gyro.
3. model plane according to claim 2 fly with seeking track navigation system automatically, it is characterised in that: described framing signal emitter adopts the discontinuous emitter of 37.5 KHz.
4. model plane according to claim 3 fly with seeking track navigation system automatically, it is characterised in that: described ground station signals Transmit-Receive Unit is provided with the receptor coordinating framing signal emitter.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620044074.XU CN205302005U (en) | 2016-01-18 | 2016-01-18 | Automatic flight of model aeroplane and model ship is with seeking track navigation |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620044074.XU CN205302005U (en) | 2016-01-18 | 2016-01-18 | Automatic flight of model aeroplane and model ship is with seeking track navigation |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205302005U true CN205302005U (en) | 2016-06-08 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620044074.XU Expired - Fee Related CN205302005U (en) | 2016-01-18 | 2016-01-18 | Automatic flight of model aeroplane and model ship is with seeking track navigation |
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| Country | Link |
|---|---|
| CN (1) | CN205302005U (en) |
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2016
- 2016-01-18 CN CN201620044074.XU patent/CN205302005U/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 | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160608 Termination date: 20170118 |
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| CF01 | Termination of patent right due to non-payment of annual fee |