CN104787349A - Aircraft safety take-off control method and device - Google Patents
Aircraft safety take-off control method and device Download PDFInfo
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- CN104787349A CN104787349A CN201510191821.2A CN201510191821A CN104787349A CN 104787349 A CN104787349 A CN 104787349A CN 201510191821 A CN201510191821 A CN 201510191821A CN 104787349 A CN104787349 A CN 104787349A
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Abstract
The invention discloses an aircraft safety take-off control method. The method comprises the steps of 10, obtaining information of an angle between an aircraft body and the horizontal plane through an angle sensor; 20, judging whether the obtained information of the angle is smaller than or equal to the maximum safety angle threshold value or not; 30, controlling the aircraft to take off if the obtained information of the angle is smaller than or equal to the maximum safety angle threshold value. The invention further discloses an aircraft safety take-off control device. By the adoption of the technical scheme, whether the aircraft is horizontally placed or not can be accurately judged, and the aircraft can safely take off.
Description
Technical field
The present invention relates to aircraft field, particularly relate to a kind of aircraft security take off control method and device.
Background technology
Aircraft (flight vehicle) is the apparatus flyer flown in endoatmosphere or space, exoatmosphere (space) being manufactured by the mankind, can fly away from ground, control in spaceflight and by people.Aircraft comprises unmanned plane during flying device etc., and this unmanned plane during flying device at automatic offline mode, manually flight module or Semi-automatic flight mode of flight, can be taken photo by plane to complete or investigate affairs.This aircraft, before executing the task and taking off, first will be placed in ground or other planes and take off; In take-off process, the software and hardware of aircraft is started working, and the power motor of aircraft starts high speed rotating, period complete machine state generation great variety of taking off, in addition the impact of external environment condition (such as wind-force etc.), very easily take off during aircraft takeoff failure or other faults.In order to make aircraft take off smoothly, the most frequently used means are as far as possible by aircraft water placing flat, but aircraft whether horizontal positioned, and user is judged by naked eyes usually, then makes aircraft be placed on level attitude according to judged result to aircraft adjustment.Can find out thus, in existing technology, judge whether aircraft is horizontal by naked eyes, easily cause judging inaccurate, and then aircraft can accurately not adjusted to level attitude, affect aircraft and take off smoothly.
Foregoing, only for auxiliary understanding technical scheme of the present invention, does not represent and admits that foregoing is prior art.
Summary of the invention
Main purpose of the present invention is to provide a kind of aircraft security take off control method and device, is intended to judge accurately aircraft whether horizontal positioned, and then aircraft security is taken off.
For achieving the above object, the invention provides a kind of aircraft security take off control method, the method comprises:
S10, obtain the angle information between described aircraft fuselage and horizontal surface by angular transducer;
S20, judge whether the angle information of described acquisition is less than or equal to maximum security standpoint threshold values;
If the angle information of the described acquisition of S30 is less than or equal to maximum security standpoint threshold values, then control described aircraft takeoff.
Preferably, after step S20, the method also comprises:
If the angle information of the described acquisition of S40 is greater than maximum security standpoint threshold values, then controls alarm module and send alerting signal, and return step S10.
Preferably, if the angle information of the described acquisition of described S40 is greater than maximum security standpoint threshold values, then controls the step that alarm module sends alerting signal and comprise:
If the angle information of the described acquisition of S41 is greater than maximum security standpoint threshold values, then the LED controlled in described alarm module is glimmered and/or the buzzer phone controlled in described alarm module sends audio-frequency information.
Preferably, if the angle information of described acquisition is less than or equal to maximum security standpoint threshold values, then after controlling the step of described aircraft takeoff or simultaneously, the method also comprises:
S50, control LED in described alarm module often bright the and buzzer phone controlled in described alarm module close.
Preferably, described angular transducer is three-axis gyroscope.
In addition, for achieving the above object, the present invention also provides a kind of aircraft security take off control device, and this device comprises angular transducer, the judge module be connected with described angular transducer, the take off control module that is connected with described judge module, wherein:
Angular transducer, for obtaining the angle information between described aircraft fuselage and horizontal surface;
Judge module, for judging whether the angle information of described acquisition is less than or equal to maximum security standpoint threshold values;
Take off control module, for when the angle information of described acquisition is less than or equal to maximum security standpoint threshold values, controls described aircraft takeoff.
Preferably, this device also comprises the alarm control module be connected with described judge module, the alarm module be connected with described alarm control module, described alarm control module is used for when the angle information of described acquisition is greater than maximum security standpoint threshold values, controls alarm module and sends alerting signal.
Preferably, described alarm module comprises LED and/or buzzer phone, described alarm control module, for when the angle information of described acquisition is greater than maximum security standpoint threshold values, the LED controlled in described alarm module is glimmered and/or the buzzer phone controlled in described alarm module sends audio-frequency information.
Preferably, described alarm control module also for when the angle information of described acquisition is less than or equal to maximum security standpoint threshold values, control LED in described alarm module often bright the and buzzer phone controlled in described alarm module close.
Preferably, described angular transducer is three-axis gyroscope.
Aircraft security take off control method of the present invention and device, obtain the angle information between described aircraft fuselage and horizontal surface by angular transducer; S20, judge whether the angle information of described acquisition is less than or equal to maximum security standpoint threshold values; If the angle information of the described acquisition of S30 is less than or equal to maximum security standpoint threshold values, then control described aircraft takeoff; The angle information between aircraft fuselage and horizontal surface can be obtained accurately by angular transducer, again the angle information of acquisition and maximum security standpoint threshold values are compared, to judge this aircraft whether horizontal positioned, when this aircraft water placing flat, control this aircraft takeoff, make aircraft can safe take-off.
Accompanying drawing explanation
Fig. 1 is the schematic flow sheet of the first embodiment of aircraft security take off control method of the present invention;
Fig. 2 is the schematic flow sheet of the second embodiment of aircraft security take off control method of the present invention;
Fig. 3 is the structural representation of the preferred embodiment of aircraft security take off control device of the present invention.
The realization of the object of the invention, functional characteristics and advantage will in conjunction with the embodiments, are described further with reference to accompanying drawing.
Detailed description of the invention
Should be appreciated that specific embodiment described herein only in order to explain the present invention, be not intended to limit the present invention.
The invention provides a kind of aircraft security take off control method, with reference to Fig. 1, in one embodiment, this aircraft security take off control method comprises:
S10, obtain the angle information between this aircraft fuselage and horizontal surface by angular transducer.
This angular transducer is three-axis gyroscope, can the cireular frequency of this aircraft of Simultaneously test in horizontal surface 4 directions by this three-axis gyroscope.This angular transducer is arranged on the middle part of aircraft fuselage, measures the angle information between this aircraft fuselage and horizontal surface by this angular transducer.
Concrete, before this aircraft is placed on ground or other plane standby for takeoffs, obtain the angle information between this aircraft fuselage and horizontal surface by angular transducer in real time.
S20, judge whether the angle information of this acquisition is less than or equal to maximum security standpoint threshold values, if the angle information of this acquisition is less than or equal to maximum security standpoint threshold values, then perform step S30.
This maximum security standpoint threshold values can pre-set, as being set to | and ± 2 ° |, namely when the angle information obtained on board the aircraft is less than or equal to | ± 2 ° | time, then can think aircraft horizontal positioned; When the angle information obtained on board the aircraft is greater than | ± 2 ° | time, then can think that aircraft there occurs inclination, not be to be in horizontal positioned state.
S30, control this aircraft takeoff.
In this step, control aircraft takeoff, the software and hardware of aircraft is started working, and performs takeoff operational.
Adopt technique scheme, the angle information that can obtain accurately between aircraft fuselage and horizontal surface is measured by angular transducer, again the angle information of acquisition and maximum security standpoint threshold values are compared, to judge this aircraft whether horizontal positioned, when this aircraft water placing flat, control this aircraft takeoff, make aircraft can safe take-off; Can avoid in prior art, by artificial judgment aircraft whether horizontal positioned easily cause the defect of error in judgement.
Further, after step S20, the method also comprises:
If the angle information of this acquisition of S40 is greater than maximum security standpoint threshold values, then controls alarm module and send alerting signal, and return step S10.
When the angle information being this acquisition in the judged result of step S20 is greater than maximum security standpoint threshold values, then think that aircraft there occurs inclination, be not be in horizontal positioned state, now need to send alerting signal, with reminding user.User is receiving this alerting signal, manually can adjust aircraft, this aircraft is adjusted to horizontal positioned as far as possible.
This alerting signal comprises aud. snl. and/or optical signal.
In this step, after control alarm module sends alerting signal, return step S10 again, continue through angular transducer and obtain angle information between this aircraft fuselage and horizontal surface, namely after user adjusts this aircraft, continue to return step S10, obtain the angle information between aircraft fuselage and horizontal surface by angular transducer.
Further, this step S40 comprises:
If the angle information of this acquisition of S41 is greater than maximum security standpoint threshold values, then the LED controlled in this alarm module is glimmered and/or the buzzer phone controlled in this alarm module sends audio-frequency information.
This alarm module comprises LED and/or buzzer phone, when the angle information obtained is greater than maximum security standpoint threshold values, can control the LED flicker in this alarm module, as bright one second goes out one second; The buzzer phone that also can control in this alarm module sends sound signal, and this sound signal can pre-set, and as yowled, three seconds stop one second, and this sound signal also can be concrete voice signal (as " aircraft inclination "); The LED that also can simultaneously control in this alarm module is glimmered and the buzzer phone controlled in this alarm module sends sound signal.User, by this alerting signal, learns that this aircraft is not in horizontal positioned intuitively, and then can manually adjust accordingly this aircraft, and this aircraft is adjusted to horizontal positioned as far as possible.
In another embodiment, this LED has four, be respectively the first LED, second LED, 3rd LED and the 4th LED, these four LED are separately positioned on four faces all around of aircraft fuselage, as the first LED is arranged on before aircraft fuselage, second LED is arranged on after aircraft fuselage, 3rd LED is arranged on the left side of aircraft fuselage, 4th LED is arranged on the right side of aircraft fuselage, when the flicker of this first LED, represent that this aircraft has turned forward, when the flicker of this second LED, represent that this aircraft has tilted backwards, when the 3rd LED flicker, represent that this aircraft has been tilted to the left, when the 4th LED flicker, represent that this aircraft has been tilted to the right.When the angle information of this acquisition is greater than maximum security standpoint threshold values, and the angle information of this acquisition is the angle information between the front direction of aircraft fuselage and horizontal surface, then can think that this aircraft there occurs inclination forward, then control the flicker of this first LED, and control the second LED, the 3rd LED and the 4th LED Chang Liang, user is when seeing that this first LED is glimmered, can learn that this aircraft there occurs inclination forward easily, and then can to aircraft adjustment, aircraft is horizontal accordingly; When the angle information of this acquisition is greater than maximum security standpoint threshold values, and the angle information of this acquisition is the angle information between the posterior direction of aircraft fuselage and horizontal surface, then can think that this aircraft there occurs inclination backward, then control the flicker of this second LED, and control the first LED, the 3rd LED and the 4th LED Chang Liang, then user is when seeing that this second LED is glimmered, can learn that this aircraft there occurs inclination backward easily, and then can to aircraft adjustment, aircraft is horizontal accordingly; When the angle information of this acquisition is greater than maximum security standpoint threshold values, and the angle information of this acquisition is the angle information between the direction, the left side of aircraft fuselage and horizontal surface, then can think that this aircraft there occurs inclination left, then control the 3rd LED flicker, and control the first LED, the second LED and the 4th LED Chang Liang, then user is when seeing the 3rd LED flicker, can learn that this aircraft there occurs inclination left easily, and then can to aircraft adjustment, aircraft is horizontal accordingly; When the angle information of this acquisition is greater than maximum security standpoint threshold values, and the angle information of this acquisition is the angle information between the right direction of aircraft fuselage and horizontal surface, then can think that this aircraft there occurs inclination to the right, then control the 4th LED flicker, and control the first LED, the second LED and the 3rd LED Chang Liang, then user is when seeing the 4th LED flicker, can learn that this aircraft there occurs inclination to the right easily, and then can to aircraft adjustment, aircraft is horizontal accordingly.
Further, as shown in Figure 2, after step S30 or simultaneously, the method also comprises:
S50, control LED in this alarm module often bright the and buzzer phone controlled in this alarm module close.
When the angle information that the judged result of step S20 is this acquisition is less than or equal to maximum security standpoint threshold values, control LED in this alarm module often bright the and buzzer phone controlled in this alarm module close.User, when watching this LED often bright and not hearing that buzzer phone is sounded, can learn that this aircraft is in horizontal positioned, can perform takeoff operational to this aircraft.
The present invention also provides a kind of aircraft security take off control device, with reference to Fig. 3, in one embodiment, this aircraft security take off control device comprises angular transducer 10, the judge module 20 be connected with this angular transducer 10, the take off control module 30 that is connected with this judge module 20, wherein:
Angular transducer 10, for obtaining the angle information between this aircraft fuselage and horizontal surface;
Judge module 20, for judging whether the angle information of this acquisition is less than or equal to maximum security standpoint threshold values;
Take off control module 30, for when the angle information of this acquisition is less than or equal to maximum security standpoint threshold values, controls this aircraft takeoff.
This angular transducer 10 is three-axis gyroscope, can the cireular frequency of this aircraft of Simultaneously test in horizontal surface 4 directions by this three-axis gyroscope.This angular transducer 10 is arranged on the middle part of aircraft fuselage, measures the angle information between this aircraft fuselage and horizontal surface by this angular transducer 10.
Concrete, before this aircraft is placed on ground or other plane standby for takeoffs, obtain the angle information between this aircraft fuselage and horizontal surface by this angular transducer 10 in real time.
This maximum security standpoint threshold values can pre-set, as being set to | and ± 2 ° |, namely when the judged result of judge module 20 is that the angle information obtained on board the aircraft is less than or equal to | ± 2 ° | time, then can think aircraft horizontal positioned; When the judged result of judge module 20 is that the angle information obtained on board the aircraft is greater than | during ± 2 ° of ︱, then can think that aircraft there occurs inclination, not be to be in horizontal positioned state.
This take off control module 30 is when the angle information that the judged result of this judge module 20 is acquisition is less than or equal to maximum security standpoint threshold values, and control aircraft takeoff, the software and hardware of aircraft is started working, and performs takeoff operational.
Further, this device also comprises the alarm control module 40 be connected with this judge module 20, the alarm module 50 be connected with this alarm control module 40, this alarm control module 40, for when the angle information of this acquisition is greater than maximum security standpoint threshold values, controls alarm module 50 and sends alerting signal.
When the angle information that the judged result of judge module 20 is this acquisition is greater than maximum security standpoint threshold values, then thinks that aircraft there occurs inclination, be not be in horizontal positioned state, now send alerting signal, with reminding user by alarm module 50.User is receiving this alerting signal, manually can adjust aircraft, this aircraft is adjusted to horizontal positioned as far as possible.
This alerting signal comprises aud. snl. and/or optical signal.
Control after alarm module 50 sends alerting signal at this alarm control module 40, this angular transducer 10 continues to obtain the angle information between this aircraft fuselage and horizontal surface, namely, after user adjusts this aircraft, continue through angular transducer 10 and obtain angle information between aircraft fuselage and horizontal surface.
Further, this alarm module 50 comprises LED and/or buzzer phone, this alarm control module 40, for when the angle information of this acquisition is greater than maximum security standpoint threshold values, the LED controlled in this alarm module 50 is glimmered and/or the buzzer phone controlled in this alarm module 50 sends audio-frequency information.
This alarm module 50 comprises LED and/or buzzer phone, when the angle information obtained is greater than maximum security standpoint threshold values, can control the LED flicker in this alarm module 50, as bright one second goes out one second; The buzzer phone that also can control in this alarm module 50 sends sound signal, and this sound signal can pre-set, and as yowled, three seconds stop one second, and this sound signal also can be concrete voice signal (as " aircraft inclination "); The LED that also can simultaneously control in this alarm module 50 is glimmered and the buzzer phone controlled in this alarm module 50 sends sound signal.User, by this alerting signal, learns that this aircraft is not in horizontal positioned intuitively, and then can manually adjust accordingly this aircraft, and this aircraft is adjusted to horizontal positioned as far as possible.
In another embodiment, this LED has four, be respectively the first LED, second LED, 3rd LED and the 4th LED, these four LED are separately positioned on four faces all around of aircraft fuselage, as the first LED is arranged on before aircraft fuselage, second LED is arranged on after aircraft fuselage, 3rd LED is arranged on the left side of aircraft fuselage, 4th LED is arranged on the right side of aircraft fuselage, when the flicker of this first LED, represent that this aircraft has turned forward, when the flicker of this second LED, represent that this aircraft has tilted backwards, when the 3rd LED flicker, represent that this aircraft has been tilted to the left, when the 4th LED flicker, represent that this aircraft has been tilted to the right.When the angle information of this acquisition is greater than maximum security standpoint threshold values, and the angle information of this acquisition is the angle information between the front direction of aircraft fuselage and horizontal surface, then can think that this aircraft there occurs inclination forward, then this alarm control module 40 controls the flicker of this first LED, and control the second LED, the 3rd LED and the 4th LED Chang Liang, user is when seeing that this first LED is glimmered, can learn that this aircraft there occurs inclination forward easily, and then can to aircraft adjustment, aircraft is horizontal accordingly; When the angle information of this acquisition is greater than maximum security standpoint threshold values, and the angle information of this acquisition is the angle information between the posterior direction of aircraft fuselage and horizontal surface, then can think that this aircraft there occurs inclination backward, then this alarm control module 40 controls the flicker of this second LED, and control the first LED, the 3rd LED and the 4th LED Chang Liang, then user is when seeing that this second LED is glimmered, can learn that this aircraft there occurs inclination backward easily, and then can to aircraft adjustment, aircraft is horizontal accordingly; When the angle information of this acquisition is greater than maximum security standpoint threshold values, and the angle information of this acquisition is the angle information between the direction, the left side of aircraft fuselage and horizontal surface, then can think that this aircraft there occurs inclination left, then this alarm control module 40 controls the 3rd LED flicker, and control the first LED, the second LED and the 4th LED Chang Liang, then user is when seeing the 3rd LED flicker, can learn that this aircraft there occurs inclination left easily, and then can to aircraft adjustment, aircraft is horizontal accordingly; When the angle information of this acquisition is greater than maximum security standpoint threshold values, and the angle information of this acquisition is the angle information between the right direction of aircraft fuselage and horizontal surface, then can think that this aircraft there occurs inclination to the right, then this alarm control module 40 controls the 4th LED flicker, and control the first LED, the second LED and the 3rd LED Chang Liang, then user is when seeing the 4th LED flicker, can learn that this aircraft there occurs inclination to the right easily, and then can to aircraft adjustment, aircraft is horizontal accordingly.
Further, this alarm control module 40 also for when the angle information of this acquisition is less than or equal to maximum security standpoint threshold values, control LED in this alarm module 50 often bright the and buzzer phone controlled in this alarm module 50 close.
When the angle information that the judged result of judge module 20 is this acquisition is less than or equal to maximum security standpoint threshold values, this alarm control module 40 control LED in this alarm module 50 often bright the and buzzer phone controlled in this alarm module 50 close.User, when watching this LED often bright and not hearing that buzzer phone is sounded, can learn that this aircraft is in horizontal positioned, can perform takeoff operational to this aircraft.
These are only the preferred embodiments of the present invention; not thereby the scope of the claims of the present invention is limited; every utilize specification sheets of the present invention and accompanying drawing content to do equivalent structure or equivalent flow process conversion; or be directly or indirectly used in other relevant technical fields, be all in like manner included in scope of patent protection of the present invention.
Claims (10)
1. an aircraft security take off control method, is characterized in that, the method comprises:
S10, obtain the angle information between described aircraft fuselage and horizontal surface by angular transducer;
S20, judge whether the angle information of described acquisition is less than or equal to maximum security standpoint threshold values;
If the angle information of the described acquisition of S30 is less than or equal to maximum security standpoint threshold values, then control described aircraft takeoff.
2. aircraft security take off control method as claimed in claim 1, it is characterized in that, after step S20, the method also comprises:
If the angle information of the described acquisition of S40 is greater than maximum security standpoint threshold values, then controls alarm module and send alerting signal, and return step S10.
3. aircraft security take off control method as claimed in claim 2, is characterized in that, if the angle information of the described acquisition of described S40 is greater than maximum security standpoint threshold values, then controls the step that alarm module sends alerting signal and comprises:
If the angle information of the described acquisition of S41 is greater than maximum security standpoint threshold values, then the LED controlled in described alarm module is glimmered and/or the buzzer phone controlled in described alarm module sends audio-frequency information.
4. aircraft security take off control method as claimed in claim 2, is characterized in that, if the angle information of described acquisition is less than or equal to maximum security standpoint threshold values, then after controlling the step of described aircraft takeoff or simultaneously, the method also comprises:
S50, control LED in described alarm module often bright the and buzzer phone controlled in described alarm module close.
5. aircraft security take off control method as claimed in claim 1, it is characterized in that, described angular transducer is three-axis gyroscope.
6. an aircraft security take off control device, is characterized in that, this device comprises angular transducer, the judge module be connected with described angular transducer, the take off control module that is connected with described judge module, wherein:
Angular transducer, for obtaining the angle information between described aircraft fuselage and horizontal surface;
Judge module, for judging whether the angle information of described acquisition is less than or equal to maximum security standpoint threshold values;
Take off control module, for when the angle information of described acquisition is less than or equal to maximum security standpoint threshold values, controls described aircraft takeoff.
7. aircraft security take off control device as claimed in claim 6, it is characterized in that, this device also comprises the alarm control module be connected with described judge module, the alarm module be connected with described alarm control module, described alarm control module is used for when the angle information of described acquisition is greater than maximum security standpoint threshold values, controls alarm module and sends alerting signal.
8. aircraft security take off control device as claimed in claim 7, it is characterized in that, described alarm module comprises LED and/or buzzer phone, described alarm control module, for when the angle information of described acquisition is greater than maximum security standpoint threshold values, the LED controlled in described alarm module is glimmered and/or the buzzer phone controlled in described alarm module sends audio-frequency information.
9. aircraft security take off control device as claimed in claim 7, it is characterized in that, described alarm control module also for when the angle information of described acquisition is less than or equal to maximum security standpoint threshold values, control LED in described alarm module often bright the and buzzer phone controlled in described alarm module close.
10. aircraft security take off control device as claimed in claim 6, it is characterized in that, described angular transducer is three-axis gyroscope.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510191821.2A CN104787349A (en) | 2015-04-21 | 2015-04-21 | Aircraft safety take-off control method and device |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510191821.2A CN104787349A (en) | 2015-04-21 | 2015-04-21 | Aircraft safety take-off control method and device |
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| CN201510191821.2A Pending CN104787349A (en) | 2015-04-21 | 2015-04-21 | Aircraft safety take-off control method and device |
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| CN105253301A (en) * | 2015-09-28 | 2016-01-20 | 深圳一电科技有限公司 | Flight control method and apparatus for multiaxial flight vehicle |
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| CN106774377A (en) * | 2017-02-07 | 2017-05-31 | 上海与德信息技术有限公司 | A kind of unmanned plane takes off control method and device |
| CN108398956A (en) * | 2018-03-23 | 2018-08-14 | 青岛中邦防务智能装备有限公司 | A kind of unmanned plane balance system and its control method for boat-carrying platform |
| CN108398956B (en) * | 2018-03-23 | 2020-12-25 | 青岛中邦防务智能装备有限公司 | Unmanned aerial vehicle balance system for shipborne platform and control method thereof |
| CN110070719A (en) * | 2019-05-08 | 2019-07-30 | 新华三技术有限公司 | A kind of license event detection method and device |
| CN110070719B (en) * | 2019-05-08 | 2021-01-08 | 新华三技术有限公司 | Traffic event detection method and device |
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