CN205139711U - Unmanned aerial vehicle safety guarantee equipment and have its unmanned aerial vehicle - Google Patents
Unmanned aerial vehicle safety guarantee equipment and have its unmanned aerial vehicle Download PDFInfo
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- CN205139711U CN205139711U CN201520878392.1U CN201520878392U CN205139711U CN 205139711 U CN205139711 U CN 205139711U CN 201520878392 U CN201520878392 U CN 201520878392U CN 205139711 U CN205139711 U CN 205139711U
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Abstract
The utility model provides an unmanned aerial vehicle safety guarantee equipment, include: a flight control system for controlling unmanned aerial vehicle sends alarm information, automatic navigates back, descend and parachuting ground in the original place, flight control system is located unmanned aerial vehicle, independent parachute -opening circuit with unmanned aerial vehicle's battery equipment with flight control system links to each other, wherein, independent parachute -opening circuit includes: a voltage reference source for exporting reference voltage, a voltage comparator, input of voltage comparater with the voltage reference source links to each other in order to insert reference voltage, another input of voltage comparater with battery equipment's output links to each other in order to insert battery voltage, voltage comparater's output with flight control system links to each other for detect the sensor module at unmanned aerial vehicle's angular speed, acceleration and inclination. The utility model discloses a pyatyi safety guarantee to unmanned aerial vehicle is realized to the last flight control system of unmanned aerial vehicle and the independent parachute -opening circuit of design.
Description
Technical field
The utility model relates to unmanned air vehicle technique field, particularly a kind of unmanned plane safety guarantee equipment and have its unmanned plane.
Background technology
Current unmanned plane security incident takes place frequently, and most of unmanned plane does not have effective security implementations.Unmanned plane crashes and not only can damage, and causes very large economic loss, also can threaten the personal safety of ground staff.The field safety precautions of present stage unmanned plane is comprehensive not enough, and it is perfectly safe to accomplish.This ignores the safety problem of unmanned plane because research staff only focuses on the performance of unmanned plane itself, even if expect increasing safety practice, also only added a level security, do not accomplish absolutely aircraft safe falling when accidents happened.
Utility model content
The purpose of this utility model is intended at least solve one of described technological deficiency.
For this reason, the purpose of this utility model is the unmanned plane proposing a kind of unmanned plane safety guarantee equipment and have it, by the independent parachute-opening circuit of the flight control system on unmanned plane and design, realizes the Pyatyi safety guarantee to unmanned plane.
To achieve these goals, the utility model embodiment on the one hand provides a kind of unmanned plane safety guarantee equipment, comprise: sending a warning for controlling unmanned plane, automatically making a return voyage, original place landing and the flight control system on parachuting ground, described flight control system is positioned on unmanned plane; Independent parachute-opening circuit, described independent parachute-opening circuit is connected with described flight control system with the battery apparatus of described unmanned plane, and wherein, described independent parachute-opening circuit comprises: for the voltage-reference of output reference voltage; Voltage comparator, an input end of described voltage comparator is connected to access described reference voltage with described voltage-reference, another input end of described voltage comparator is connected to access cell voltage with the output terminal of described battery apparatus, the output terminal of described voltage comparator is connected with described flight control system, with judging that described cell voltage exports parachute-opening instruction lower than during described reference voltage to described flight control system, controlled the parachuting equipment automatic deployment of described unmanned plane by described flight control system; For detecting the sensor assembly at the angular velocity of described unmanned plane, acceleration and inclination angle, described sensor assembly is connected with described flight control system.
Further, described voltage-reference is three end adjustable shunt formula reference sources.
Further, described flight control system is also connected with the battery apparatus of described unmanned plane the dump energy detecting described battery apparatus.
Further, described sensor assembly comprises: 3 axle gyroscopes, 3 axle accelerators and inclination angle detection circuit.
The utility model also proposes a kind of unmanned plane, comprises the unmanned plane safety guarantee equipment that above-described embodiment provides, and described unmanned plane safety guarantee equipment is connected with parachuting equipment with the battery apparatus of unmanned plane.
According to unmanned plane safety guarantee equipment and the unmanned plane of the utility model embodiment, by the independent parachute-opening circuit of the flight control system on unmanned plane and design, realize Pyatyi safety guarantee to unmanned plane, comprise alarm, make a return voyage, original place landing, parachuting, independent circuits parachuting.By above-mentioned Pyatyi safety guarantee, making to run in unmanned plane during flying process any emergency situations can safe landing, improves unmanned plane during flying safety coefficient.
The aspect that the utility model is additional and advantage will part provide in the following description, and part will become obvious from the following description, or be recognized by practice of the present utility model.
Accompanying drawing explanation
Above-mentioned and/or additional aspect of the present utility model and advantage will become obvious and easy understand from accompanying drawing below combining to the description of embodiment, wherein:
Fig. 1 is the structural drawing of the unmanned plane safety guarantee equipment according to the utility model embodiment;
Fig. 2 is the circuit diagram of the voltage-reference according to the utility model embodiment;
Fig. 3 is the circuit diagram of the voltage comparator according to the utility model embodiment;
Fig. 4 is the Pyatyi workflow diagram of the unmanned plane safety guarantee equipment according to the utility model embodiment.
Embodiment
Be described below in detail embodiment of the present utility model, the example of described embodiment is shown in the drawings, and wherein same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Be exemplary below by the embodiment be described with reference to the drawings, be intended to for explaining the utility model, and can not be interpreted as restriction of the present utility model.
As shown in Figure 1, the unmanned plane safety guarantee equipment of the utility model embodiment, comprising: flight control system 1, independent parachute-opening circuit 2 and sensor assembly 3.
Particularly, flight control system 1 is positioned on unmanned plane, sending a warning for controlling unmanned plane, automatically making a return voyage, original place landing and parachuting ground.
Independent parachute-opening circuit is connected with flight control system 1 with the battery apparatus of unmanned plane, comprising: voltage comparator U1 and voltage-reference U2.
As shown in Figure 2, voltage-reference U1 is used for output reference voltage V_REF.In an embodiment of the present utility model, voltage-reference U1 can be three end adjustable shunt formula reference sources.Such as, model is the reference source of TL431.
As shown in Figure 3, being connected with voltage-reference U1 of one of voltage comparator U2 input, reference voltage V _ REF is accessed.Being connected with the output terminal of battery apparatus of another input of voltage comparator U2, access cell voltage V_BAT.The output terminal of battery comparer U2 is connected with flight control system 1, when judging cell voltage V_BAT lower than reference voltage V _ REF, exports parachute-opening instruction to flight control system 1, is controlled the parachuting equipment automatic deployment of unmanned plane by flight control system 1.
In an embodiment of the present utility model, voltage comparator U2 can be the twin voltage comparer integrated circuit of LM393 for model.
Further, flight control system 1 is also connected with the battery apparatus of unmanned plane the dump energy detecting battery apparatus.
Sensor assembly 3 is connected with flight control system 1, for detecting the angular velocity of unmanned plane, acceleration and inclination angle.Particularly, when sensor assembly 3 detects that unmanned plane angle of inclination exceedes predetermined angle, then judge that unmanned plane breaks down.Wherein, predetermined angle is such as 70 degree.Now, sensor assembly 3 sends failure message to flight control system 1, and flight control system 1 is according to the failure message received, and landing opened by control motor stalling and parachute.
Preferably, sensor assembly 3 comprises: 3 axle gyroscopes, 3 axle accelerators and inclination angle detection circuit.Wherein, sensor assembly 3 can adopt model to be the 9 axle motion process sensors of MPU-6000 (6050).
Below with reference to Fig. 4, the Pyatyi workflow of the unmanned plane safety guarantee equipment of the utility model embodiment is described.
The first order: alarm.
When flight control system 1 detects the dump energy of battery apparatus, when detecting that unmanned plane electricity is about to exhaust, flight control system 1 controls unmanned plane control center can beam back warning information earthward, thus reminds ground staff to handle unmanned plane and make a return voyage.
The second level: make a return voyage.
Independently make a return voyage and refer to that unmanned plane does not need manual control, auto-returned appointed place.
When flight control system 1 detects that the electricity of unmanned plane reduces further, and to ground operator give the alarm do not obtain respond time, guarantee inherently safe, flight control system 1 will automatically perform order of making a return voyage, auto-returned departure location.
The third level, lands in original place.
When flight control system 1 detects that electricity is not enough to return takeoff point, unmanned plane can automatically perform original place landing order.
The fourth stage, parachuting.
When flight control system 1 detects that unmanned plane breaks down, cannot perform when making a return voyage order, control motor stalling, rapid parachute-opening, ground is gone back in parachuting.Parachuting utilizes the parachuting such as parachute or propeller-parachuting to equip the form implementing landing.
Level V, independent circuits parachuting
When flight control system 1 detects that unmanned plane breaks down, when cannot detect the need of parachute-opening, by independent parachute-opening circuit 2
By voltage comparator U2, cell voltage V_BAT and reference voltage V _ REF being compared, when judging cell voltage V_BAT lower than reference voltage V _ REF, detecting that battery is in low-voltage state, export low and high level, control parachuting equipment automatic deployment.Wherein, reference voltage V _ REF can be the warning value of default cell voltage.
The utility model also proposes a kind of unmanned plane, comprises the unmanned plane safety guarantee equipment that above-described embodiment provides, and this unmanned plane safety guarantee equipment is connected with parachuting equipment with the battery apparatus of unmanned plane.
According to unmanned plane safety guarantee equipment and the unmanned plane of the utility model embodiment, by the independent parachute-opening circuit of the flight control system on unmanned plane and design, realize Pyatyi safety guarantee to unmanned plane, comprise alarm, make a return voyage, original place landing, parachuting, independent circuits parachuting.By above-mentioned Pyatyi safety guarantee, making to run in unmanned plane during flying process any emergency situations can safe landing, improves unmanned plane during flying safety coefficient.
In the description of this instructions, specific features, structure, material or feature that the description of reference term " embodiment ", " some embodiments ", " example ", " concrete example " or " some examples " etc. means to describe in conjunction with this embodiment or example are contained at least one embodiment of the present utility model or example.In this manual, identical embodiment or example are not necessarily referred to the schematic representation of above-mentioned term.And the specific features of description, structure, material or feature can combine in an appropriate manner in any one or more embodiment or example.
Although illustrate and described embodiment of the present utility model above, be understandable that, above-described embodiment is exemplary, can not be interpreted as restriction of the present utility model, those of ordinary skill in the art can change above-described embodiment when not departing from principle of the present utility model and aim, revising, replacing and modification in scope of the present utility model.Scope of the present utility model is by claims extremely equivalency.
Claims (5)
1. a unmanned plane safety guarantee equipment, is characterized in that, comprising:
Sending a warning for controlling unmanned plane, automatically making a return voyage, original place landing and the flight control system on parachuting ground, described flight control system is positioned on unmanned plane;
Independent parachute-opening circuit, described independent parachute-opening circuit is connected with described flight control system with the battery apparatus of described unmanned plane, and wherein, described independent parachute-opening circuit comprises:
For the voltage-reference of output reference voltage;
Voltage comparator, an input end of described voltage comparator is connected to access described reference voltage with described voltage-reference, another input end of described voltage comparator is connected to access cell voltage with the output terminal of described battery apparatus, the output terminal of described voltage comparator is connected with described flight control system, with judging that described cell voltage exports parachute-opening instruction lower than during described reference voltage to described flight control system, controlled the parachuting equipment automatic deployment of described unmanned plane by described flight control system;
For detecting the sensor assembly at the angular velocity of described unmanned plane, acceleration and inclination angle, described sensor assembly is connected with described flight control system.
2. unmanned plane safety guarantee equipment as claimed in claim 1, it is characterized in that, described voltage-reference is three end adjustable shunt formula reference sources.
3. unmanned plane safety guarantee equipment as claimed in claim 1, it is characterized in that, described flight control system is also connected with the battery apparatus of described unmanned plane the dump energy detecting described battery apparatus.
4. unmanned plane safety guarantee equipment as claimed in claim 1, it is characterized in that, described sensor assembly comprises: 3 axle gyroscopes, 3 axle accelerators and inclination angle detection circuit.
5. a unmanned plane, is characterized in that, comprising: the unmanned plane safety guarantee equipment described in any one of claim 1-4, and described unmanned plane safety guarantee equipment is connected with parachuting equipment with the battery apparatus of unmanned plane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520878392.1U CN205139711U (en) | 2015-11-05 | 2015-11-05 | Unmanned aerial vehicle safety guarantee equipment and have its unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520878392.1U CN205139711U (en) | 2015-11-05 | 2015-11-05 | Unmanned aerial vehicle safety guarantee equipment and have its unmanned aerial vehicle |
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| CN205139711U true CN205139711U (en) | 2016-04-06 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106227083A (en) * | 2016-07-20 | 2016-12-14 | 广东容祺智能科技有限公司 | A kind of unmanned plane motor phase failure monitoring and protecting device |
| CN106483970A (en) * | 2016-12-23 | 2017-03-08 | 徐州飞梦电子科技有限公司 | A kind of protection device of unmanned plane inclination maximum and method |
| CN108116686A (en) * | 2018-01-17 | 2018-06-05 | 西安九天无限智能科技有限公司 | A kind of application method of the auxiliary system based on unmanned plane fixed point parachuting |
| CN108313313A (en) * | 2018-01-26 | 2018-07-24 | 重庆邮电大学 | Unmanned plane failure response system |
-
2015
- 2015-11-05 CN CN201520878392.1U patent/CN205139711U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106227083A (en) * | 2016-07-20 | 2016-12-14 | 广东容祺智能科技有限公司 | A kind of unmanned plane motor phase failure monitoring and protecting device |
| CN106483970A (en) * | 2016-12-23 | 2017-03-08 | 徐州飞梦电子科技有限公司 | A kind of protection device of unmanned plane inclination maximum and method |
| CN108116686A (en) * | 2018-01-17 | 2018-06-05 | 西安九天无限智能科技有限公司 | A kind of application method of the auxiliary system based on unmanned plane fixed point parachuting |
| CN108313313A (en) * | 2018-01-26 | 2018-07-24 | 重庆邮电大学 | Unmanned plane failure response system |
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| 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: 20160406 Termination date: 20171105 |