CN113998125A - Series power supply control system of aircraft - Google Patents
Series power supply control system of aircraft Download PDFInfo
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- CN113998125A CN113998125A CN202111352865.0A CN202111352865A CN113998125A CN 113998125 A CN113998125 A CN 113998125A CN 202111352865 A CN202111352865 A CN 202111352865A CN 113998125 A CN113998125 A CN 113998125A
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- 230000000630 rising effect Effects 0.000 claims abstract description 3
- 238000000034 method Methods 0.000 claims description 8
- 238000012544 monitoring process Methods 0.000 claims description 4
- 230000001174 ascending effect Effects 0.000 claims description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 150000001875 compounds Chemical class 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D41/00—Power installations for auxiliary purposes
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Charge And Discharge Circuits For Batteries Or The Like (AREA)
Abstract
The invention discloses a serial power supply control system of an aircraft, which is used for driving the aircraft to fly and comprises a first motor, a second motor and a third motor, wherein the first motor is used for driving the aircraft to vertically lift and hover; the second motor is used for driving the aircraft to cruise horizontally; the main battery is used for providing working power supply for the first motor and the second motor; the normal-pressure guide path is arranged at the current output end of the main battery; the pressurizing guide path is connected with the normal pressure guide path in series, and a pressurizing battery and a controllable switch are arranged on the pressurizing guide path; and the flight controller is connected with the controllable switch, when the aircraft is in a rising state, a hovering state and a horizontal cruising state, the main battery supplies power to the first motor and the second motor through the normal-pressure guide way, when the aircraft is in a landing state, the flight controller controls the controllable switch to be closed, and the main battery supplies power to the first motor and the second motor through the pressurizing guide way. The invention can provide sufficient voltage for the motor of the aircraft during landing, improve the safety of the aircraft and avoid the crash of the aircraft.
Description
Technical Field
The invention relates to the technical field of aircraft power supply, in particular to a serial power supply control system of an aircraft.
Background
The existing vertical take-off and landing aircraft are mostly powered by batteries, a typical multi-rotor aircraft and a vertical take-off and landing fixed wing aircraft are taken as examples, the multi-rotor aircraft usually uses the same set of power system when taking off and landing, the vertical take-off and landing fixed wing aircraft is usually provided with a vertical motor and a cruise motor, the vertical motor is used for providing power for taking off and landing of the aircraft, and the cruise motor is used for providing power when the aircraft enters a cruise state after reaching a sufficient height. When the aircraft can meet the system requirement of power in the takeoff stage, the battery voltage is close to exhaustion in the landing stage after long-time cruising, the battery electric quantity is increased, the internal resistance of the battery is increased, the voltage of the battery is reduced, and the vertical landing stage needs huge power to maintain balanced landing, so that the battery pack voltage is further reduced, a vertical motor of the aircraft can face the problem of insufficient voltage of a power system, and the safety performance of the aircraft is reduced even the aircraft is crashed due to insufficient power in the vertical landing process.
Disclosure of Invention
The present invention is directed to solving at least one of the problems of the prior art. Therefore, the invention provides a series power supply control system of an aircraft, which is used for driving the aircraft to fly, so that the voltage output by a power supply system can be kept consistent between the stage of low electric quantity and the stage of high electric quantity of a main battery, the aircraft is prevented from being crashed due to insufficient voltage when the aircraft lands, and the safety of the aircraft is improved.
In addition, the invention also provides a control method of the aircraft and the aircraft.
According to a first aspect embodiment of the invention, an aircraft series power control system comprises:
the first motor is used for driving the aircraft to vertically ascend and descend and hover;
the second motor is used for driving the aircraft to cruise horizontally;
the main battery is respectively connected with the first motor and the second motor and provides working power for the first motor and the second motor;
the normal-pressure guide path is arranged at the current output end of the main battery;
the pressurization guide path is arranged at the current output end of the main battery, the pressurization guide path and the normal pressure guide path are connected in series, a pressurization battery and a controllable switch are arranged on the pressurization guide path, and the controllable switch acts to enable the pressurization battery to be connected into a power supply loop of the main battery;
the flight controller is used for monitoring and controlling the operation of the aircraft, the flight controller is connected with the controllable switch, and when the aircraft is in a rising state, a hovering state and a horizontal cruising state, the main battery supplies power to the first motor and the second motor through the normal-pressure guide circuit; when the aircraft is in a landing state, the flight controller controls the controllable switch to be closed, and the main battery supplies power to the first motor and the second motor through the pressurizing guide.
The tandem type power supply control system of the aircraft according to the embodiment of the invention has at least the following beneficial effects: the aircraft needs the power supply system to provide enough voltage in the landing stage, and the main battery flies for a long time, so that the internal resistance of the main battery unit is increased, the voltage is reduced, and the sufficient voltage cannot be provided for the first motor of the aircraft. When the flight controller detects that electrical power generating system's voltage is not enough, electrical power generating system closes controllable switch, makes pressurization battery and main battery establish ties, increases electrical power generating system's voltage, improves the security of aircraft, avoids the insufficient aircraft crash that leads to of voltage.
According to the tandem power control system of the aircraft in the embodiment of the first aspect of the invention, the voltage value of the pressurized battery is smaller than that of the main battery, so that the weight of the aircraft can be reduced, and the endurance can be increased.
According to the tandem power control system of the aircraft in the embodiment of the first aspect of the invention, the voltage value of the pressurized battery is one half to one fourth of the voltage value of the main battery, and the pressurized battery is used for supplementing the problem of insufficient power of the main battery due to voltage reduction.
According to the tandem power control system of the aircraft in the embodiment of the first aspect of the invention, the pressurization guide path is provided with the unidirectional current element, and the unidirectional current element enables the main battery and the pressurization battery to form a tandem battery pack.
According to the tandem type power supply control system of the aircraft, the number of the first motors is at least four, and the load of the aircraft can be increased and the flight stability of the aircraft can be improved by using the plurality of first motors.
According to the tandem type power supply control system of the aircraft, the first motor and the second motor are respectively provided with the speed regulators, so that the rotating speeds of the first motor and the second motor can be better controlled by the speed regulators, and the stability of the aircraft is further improved.
According to the tandem power control system of an aircraft in an embodiment of the first aspect of the invention, the first motor and the second motor are respectively connected in parallel with the main battery.
In a second aspect, the present embodiment also provides a control method for an aircraft, the control method including:
reading the state of the aircraft, monitoring and reading the state of the aircraft by the flight controller, and selecting the following power supply modes according to the state of the aircraft:
the main battery supplies power to the first motor and the second motor through the normal-pressure guide circuit when the aircraft is in ascending, hovering and horizontal cruising states;
and when the aircraft is in a landing state, the flight controller controls the controllable switch to be closed, and the main battery supplies power to the first motor and the second motor through the pressurizing guide way.
The control method of the embodiment of the application has at least the following effects: by applying the control method, the flight controller monitors and acquires the electric quantity of the main battery, when the electric quantity of the main battery is lower and cannot provide enough voltage for the landing stage of the aircraft, the main battery controls the controllable switch to be closed, the booster battery is connected into the power supply system, the voltage of the power supply system is increased, and the first motor and the second motor are prevented from being crashed due to insufficient voltage in the landing stage. The pressurized battery is added to the aircraft, so that the safety of the aircraft can be improved, and the pressurized battery can supplement the problem of insufficient power of the main battery due to voltage reduction.
The aircraft according to the third aspect embodiment of the invention comprises the series power control system of the aircraft according to the first aspect embodiment of the invention.
The aircraft according to the embodiment of the third aspect of the invention has at least the following advantages: the aircraft of the embodiment comprises the series power supply control system of the aircraft, so that when the voltage of a main battery of the aircraft is insufficient, a voltage can be supplemented for the power supply system by a pressurized battery in the power supply system, the safety of the aircraft is ensured, and the probability of crash of the aircraft caused by insufficient voltage of the power supply system is reduced. The safety of the aircraft is improved without increasing a main battery, so that the weight of the battery pack is reduced, and the carrying capacity and the voyage time of the multi-rotor aircraft are improved.
Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.
Drawings
The invention is further described with reference to the following figures and examples, in which:
fig. 1 is a series power control system of an aircraft according to an embodiment of the present invention.
Reference numerals: a main battery 100; a pressurized battery 110; a speed governor 120; a first motor 130; a second motor 140; a unidirectional current element 150; a controllable switch 160.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the accompanying drawings are illustrative only for the purpose of explaining the present invention, and are not to be construed as limiting the present invention.
In the description of the present invention, it should be understood that the orientation or positional relationship referred to in the description of the orientation, such as the upper, lower, front, rear, left, right, etc., is based on the orientation or positional relationship shown in the drawings, and is only for convenience of description and simplification of description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.
In the description of the present invention, the meaning of a plurality of means is one or more, the meaning of a plurality of means is two or more, and larger, smaller, larger, etc. are understood as excluding the number, and larger, smaller, inner, etc. are understood as including the number. If the first and second are described for the purpose of distinguishing technical features, they are not to be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated or implicitly indicating the precedence of the technical features indicated.
In the description of the present invention, unless otherwise explicitly limited, terms such as arrangement, installation, connection and the like should be understood in a broad sense, and those skilled in the art can reasonably determine the specific meanings of the above terms in the present invention in combination with the specific contents of the technical solutions.
Referring to fig. 1, the present invention provides a preferred embodiment of a tandem power control system for an aircraft, which includes a main battery 100, a pressurized battery 110, a first motor 130, a second motor 140, a speed regulator 120, a unidirectional current element 150, and a controllable switch 160.
Specifically, the first motor 130 provides power for vertical lifting and hovering of the aircraft, the second motor 140 provides power for horizontal cruising of the aircraft, when the aircraft is about to take off, the main battery 100 directly supplies power to the first motor 130, a current output end of the main battery 100 is connected with a current input end of the first motor 130 of the aircraft through a lead, and the main battery 100 directly drives the first motor 130, so that the aircraft can take off vertically. The current output end of the main battery 100 is connected with the second motor 140 of the aircraft through a lead, and the current output end of the pressurizing battery 110 is connected with the current input end of the main battery 100 in series through a lead, so that in the landing stage of the aircraft, as the aircraft flies for a long time, the electric quantity in the power supply system is more consumed, the internal resistance of the main battery 100 is increased, the voltage of the main battery 100 is reduced, and the sufficient voltage cannot be provided for the first motor 130 in the landing stage. When the flight controller detects that the main battery 100 cannot provide enough voltage for the first motor 130, the power supply system closes the controllable switch 160, and the pressurized battery 110 is connected in series with the main battery 100, so that the voltage of the power supply system is increased, and enough voltage is provided for the first motor 130, and under the enough voltage, the first motor 130 can drive the aircraft to stably land, thereby avoiding the aircraft from being crashed.
Further, the main battery 100 is respectively connected with the first motor 130 and the second motor 140, the main battery 100 provides power for the first motor 130 and the second motor 104 when working, the main battery 100 is arranged on the normal pressure guide path, the pressurizing battery 110 is arranged on the pressurizing guide path, the pressurizing guide path is connected with the normal pressure guide path in series, when the aircraft is in the stages of taking off, hovering and cruising, the main battery 100 supplies power to the first motor 130 and the second motor 140 through the normal pressure guide path, when the aircraft is in the stage of landing, the flight controller controls the controllable switch 160 to be closed, so that the pressurizing guide path and the normal pressure guide path are in the state of being connected in series, and the main battery 100 is connected with the pressurizing battery 110 in series, thereby increasing the output voltage of the power supply system and ensuring that the aircraft can land safely.
Referring to fig. 1, the voltage value of the pressurized battery 110 is smaller than that of the main battery 100, and the initial voltage of the main battery 100 is sufficient in the takeoff phase of the aircraft, but in the landing phase of the aircraft, the main battery 100 is nearly dead, the internal resistance of the battery is increased, so that the voltage is insufficient, and under the condition of insufficient voltage, the pressurized battery 110 is connected with the main battery 100 in series by the power supply system, so that the power output of the power supply system can be effectively improved, and the stability of the aircraft is improved.
Specifically, the voltage value of the pressurized battery 110 is equal to one-half to one-fourth of the initial voltage of the main battery 100, the electric quantity of the battery is sufficient in the takeoff phase of the aircraft, the power supply system can provide sufficient voltage for the takeoff phase and the cruise phase of the aircraft, the electric quantity of the battery is nearly exhausted in the landing phase of the aircraft, the internal resistance of the battery is increased, the voltage of the battery is reduced, the sufficient voltage cannot be provided for the first motor 130 of the aircraft in the landing phase, and when the power supply system judges that the voltage of the main battery 100 is insufficient, the power supply system controls the controllable switch 160, so that the pressurized battery 110 is connected in series with the main battery 100, the voltage of the power supply system is increased, the sufficient voltage is provided for the first motor 130, and the safe landing of the aircraft is ensured. In some embodiments, the voltage of the pressurized battery 110 is much lower than the voltage of the main battery 100, for example, the voltage when the main battery 100 lands is lower by 30V than the voltage when the main battery 100 takes off, and the power supply system can provide enough voltage for the first motor 130 only by using the pressurized battery 110 with the voltage of 30V, so as to ensure that the aircraft lands smoothly.
In some embodiments, the number of the first motors 130 is at least four, and the number of the first motors 130 may be greater than four, so long as the first motors 130 can provide enough lift for the aircraft, and the first motors 130 should be symmetrically arranged to ensure that the aircraft can ascend smoothly. It is understood that the number of the second motors 140 can be more than two, and the arrangement of more than two second motors 140 can improve the cruising speed of the aircraft.
Referring to fig. 1, the pressurizing guide path where the pressurizing battery 110 is located is provided with a unidirectional current element 150, the unidirectional current element 150 limits the pressurizing battery 110 not to supply power to the second motor 140, the pressurizing battery 110 does not supply power to the second motor 140 during the cruising phase of the aircraft, therefore, the pressurizing battery 110 does not reduce the power during the cruising phase, the power of the pressurizing battery 110 can be maintained at a higher level, when the aircraft lands vertically or during the insufficient voltage phase, the pressurizing battery 110 is connected to the power supply system, and the pressurizing battery 110 and the main battery 100 jointly supply power to the first motor 130. In some embodiments, the time that the aircraft is maintained in the cruise phase is short, the power consumption of the aircraft for the main battery 100 is small, the power consumption of the main battery 100 is small, and during the landing phase of the aircraft, since the main battery 100 maintains a high power, the main battery 100 can provide sufficient voltage for the first motor 130, and the pressurized battery 110 is not needed to supply power to the power system, in which case, the pressurized battery 110 does not need to be connected to the power system, and only the main battery 100 supplies power to the first motor 130.
In some embodiments, the battery capacity of the pressurized battery 110 is smaller than the battery capacity of the main battery 100, the weight of the pressurized battery 110 is lighter than the weight of the main battery 100, and the lighter pressurized battery 110 can reduce the overall weight of the aircraft, improve the endurance of the aircraft, improve the carrying capacity of the aircraft, and further improve the performance of the aircraft. This electrical power generating system is applied to many rotor unmanned aerial vehicle, and this electrical power generating system also can be applied to compound wing unmanned aerial vehicle.
Referring to fig. 1, the first motor 130 and the second motor 140 are provided with a speed governor 120, and the speed governor 120 is an electronic speed governor, and in some embodiments, the speed governor 120 may use a brushed electronic speed governor or a brushless electronic speed governor, which controls the speed of the motors and, by adjusting the speed of the motors, controls the starting, stopping, and braking of the aircraft.
Based on this, the present application provides an aircraft control method, when the aircraft is in a flight state, the flight controller monitors and reads the state of the aircraft, when the aircraft is in a rise, hover and horizontal cruise state, the main battery 100 supplies power to the first motor 130 and the second motor 140 through the normal pressure guide, when the aircraft is in a landing stage, the controllable switch 160 is closed, and the main battery 100 supplies power to the first motor 130 and the second motor 140 through the pressurization guide.
The embodiments of the present invention have been described in detail with reference to the accompanying drawings, but the present invention is not limited to the above embodiments, and various changes can be made within the knowledge of those skilled in the art without departing from the gist of the present invention.
Claims (9)
1. An in-line power control system for an aircraft for propelling the aircraft, comprising:
the first motor is used for driving the aircraft to vertically ascend and descend and hover;
the second motor is used for driving the aircraft to cruise horizontally;
the main battery is respectively connected with the first motor and the second motor and provides working power for the first motor and the second motor;
the normal-pressure guide path is arranged at the current output end of the main battery;
the pressurization guide path is arranged at the current output end of the main battery, the pressurization guide path and the normal pressure guide path are connected in series, a pressurization battery and a controllable switch are arranged on the pressurization guide path, and the controllable switch acts to enable the pressurization battery to be connected into a power supply loop of the main battery;
the flight controller is used for monitoring and controlling the operation of the aircraft, the flight controller is connected with the controllable switch, and when the aircraft is in a rising state, a hovering state and a horizontal cruising state, the main battery supplies power to the first motor and the second motor through the normal-pressure guide circuit; when the aircraft is in a landing state, the flight controller controls the controllable switch to be closed, and the main battery supplies power to the first motor and the second motor through the pressurizing guide.
2. The tandem power control system for an aircraft according to claim 1, wherein the voltage value of the pressurized battery is smaller than the voltage value of the main battery.
3. The tandem power control system for an aircraft according to claim 2, wherein the voltage value of the pressurized battery is one half to one quarter of the initial voltage value of the main battery.
4. The tandem power control system for an aircraft according to claim 1, wherein the pressurization guide path is provided with a unidirectional current element.
5. The tandem power control system for an aircraft of claim 1, wherein said first motors are at least four in number.
6. An aircraft series power control system according to claim 1, wherein the first and second motors are each provided with a speed governor.
7. The tandem power control system for an aircraft according to claim 1, wherein said first motor and said second motor are connected in parallel to said main battery, respectively.
8. A method for controlling an aircraft, characterized in that,
reading the state of the aircraft, monitoring and reading the state of the aircraft by the flight controller, and selecting the following power supply modes according to the state of the aircraft:
the main battery supplies power to the first motor and the second motor through the normal-pressure guide circuit when the aircraft is in ascending, hovering and horizontal cruising states;
and when the aircraft is in a landing state, the flight controller controls the controllable switch to be closed, and the main battery supplies power to the first motor and the second motor through the pressurizing guide way.
9. An aircraft comprising an in-line power control system for an aircraft according to any one of claims 1 to 7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111352865.0A CN113998125A (en) | 2021-11-16 | 2021-11-16 | Series power supply control system of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111352865.0A CN113998125A (en) | 2021-11-16 | 2021-11-16 | Series power supply control system of aircraft |
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| Publication Number | Publication Date |
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| CN113998125A true CN113998125A (en) | 2022-02-01 |
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| CN202111352865.0A Pending CN113998125A (en) | 2021-11-16 | 2021-11-16 | Series power supply control system of aircraft |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20160039300A1 (en) * | 2014-08-08 | 2016-02-11 | SZ DJI Technology Co., Ltd | Systems and methods for uav battery power backup |
| CN109515726A (en) * | 2018-12-25 | 2019-03-26 | 汇星海科技（天津）有限公司 | A kind of unmanned plane electrical source of power switching circuit plate and its switching method |
| WO2020035042A1 (en) * | 2018-08-17 | 2020-02-20 | 深圳市道通智能航空技术有限公司 | Power supply method and device for aircraft, flight control system, and aircraft |
| CN112644717A (en) * | 2019-10-09 | 2021-04-13 | 肇庆凌飞航空科技有限公司 | One-way parallel electric composite wing aircraft double-power-supply system |
| CN217374909U (en) * | 2021-11-16 | 2022-09-06 | 肇庆凌飞航空科技有限公司 | Tandem type power supply control system of aircraft and aircraft |
-
2021
- 2021-11-16 CN CN202111352865.0A patent/CN113998125A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20160039300A1 (en) * | 2014-08-08 | 2016-02-11 | SZ DJI Technology Co., Ltd | Systems and methods for uav battery power backup |
| WO2020035042A1 (en) * | 2018-08-17 | 2020-02-20 | 深圳市道通智能航空技术有限公司 | Power supply method and device for aircraft, flight control system, and aircraft |
| CN109515726A (en) * | 2018-12-25 | 2019-03-26 | 汇星海科技（天津）有限公司 | A kind of unmanned plane electrical source of power switching circuit plate and its switching method |
| CN112644717A (en) * | 2019-10-09 | 2021-04-13 | 肇庆凌飞航空科技有限公司 | One-way parallel electric composite wing aircraft double-power-supply system |
| CN217374909U (en) * | 2021-11-16 | 2022-09-06 | 肇庆凌飞航空科技有限公司 | Tandem type power supply control system of aircraft and aircraft |
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