CN111452981A - Redundant vertical starting power system of composite vertical take-off and landing aircraft and layout method thereof - Google Patents
Redundant vertical starting power system of composite vertical take-off and landing aircraft and layout method thereof Download PDFInfo
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- 230000005611 electricity Effects 0.000 claims description 7
- 238000009434 installation Methods 0.000 claims description 2
- 239000000446 fuel Substances 0.000 abstract description 3
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
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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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/40—Arrangements for mounting power plants in aircraft
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Abstract
The invention discloses a redundant vertical starting power system of a combined type vertical take-off and landing aircraft and a layout method thereof. The invention has the following beneficial effects: the power redundancy and the actuating mechanism redundancy of the system are increased, and the manufacturing cost is reduced; the redundancy safety is improved, and the accident rate is reduced; the space of load and fuel is not occupied, and the utilization rate of the space of the aircraft body and the flight time are improved.
Description
Technical Field
The invention relates to a redundant vertical starting power system of a combined type vertical take-off and landing aircraft and a layout method thereof, belonging to the technical field of power systems of combined type vertical take-off and landing aircraft.
Background
At present, most of common composite vertical take-off and landing aircrafts in the market adopt four rotors to provide lift force in the vertical take-off and landing stage, and four rotor motors are respectively installed on two sides of an aircraft body and hung in tail stay rods parallel to the aircraft body on wings. The tail stay is generally a solid or hollow carbon rod, aluminum profile or other self-made slender rod, and only plays a role of fixing the vertical motor, and an electronic speed regulator and a power battery for controlling the rotation of the motor are generally fixed in the aircraft fuselage.
A common layout method of a vertical take-off and landing power system of a combined type vertical take-off and landing aircraft mainly aims at the aircraft with the take-off weight less than or equal to 50kg, 2 6S batteries are connected in series to form a 12S (48V) battery pack and simultaneously supply power to 4 rotor motors, and the total hovering current is within 200 amperes. For the composite vertical take-off and landing aircraft with the take-off weight within the range of 50-180kg, if 4 rotors are still adopted to provide lift force, the following defects exist:
(1) the requirement of the pulling force (power) of a single motor is increased, even the current motor shelf product cannot meet the requirement, customized development is achieved, and the cost is increased;
(2) to provide more lift, the rotor diameter needs to be increased, and if the tail boom length is increased asynchronously, the tip of the rotor physically interferes with the fuselage section. Meanwhile, the larger the rotor diameter is, the larger the rotational inertia is, and the lower the response frequency is, which is not favorable for the control frequency requirement of the vertical power system above 200 HZ.
(3) The total current of hovering increases, and according to joule's law, the heat that the electric current produced through the conductor is known with the square of electric current is directly proportional, and the energy that the battery provided has a great part to waste through the form of heat energy, and energy utilization efficiency reduces.
(4) To reduce the voltage drop and energy loss on the wires, the battery supply voltage has to be increased to 24S (96V). Due to the lack of shelf charger products supporting 12S or 24S batteries in the market at present, 4 6S batteries are generally connected in series to form a 24S (96V) battery pack to supply power to the rotor motor, so that the complexity of the system and the single-node failure rate are increased.
(5) The increase of the battery pack can extrude the space of load and fuel oil, and the utilization rate of the space of the machine body is reduced.
Disclosure of Invention
The technical problem to be solved by the invention is to provide a redundant vertical starting power system of a composite vertical take-off and landing aircraft and a layout method thereof, wherein the system can utilize the existing market shelf products to the maximum extent and reduce the manufacturing cost; the overall dimension of the aircraft is reduced, and the transportation and the storage are convenient; the redundancy safety is improved, and the accident rate is reduced; the electric regulating unit ESC, the motor and the battery are fixed at positions outside the aircraft body, so that the load and fuel space is not occupied, and the utilization rate of the aircraft body space and the flight time are improved.
The invention is realized by the following scheme: the redundant start power system that hangs down of combined type VTOL aircraft, it includes the redundant system of actuating mechanism and the redundant system of power supply, the redundant system of actuating mechanism and the redundant system of power supply all set up on the tail vaulting pole of aircraft, the redundant system of actuating mechanism includes upper rotor driving system actuating mechanism and lower floor's rotor driving system actuating mechanism, upper rotor driving system actuating mechanism with lower floor's rotor driving system actuating mechanism all includes a plurality of motors, all installs the rotor that corresponds on every motor, two liang of adjacent motor rotation direction of upper rotor driving system actuating mechanism are opposite, two liang of adjacent motor rotation direction of lower floor's rotor driving system actuating mechanism are also opposite.
The electric regulating group ESC, the motor and the battery are fixed at positions outside the fuselage.
The ESC of electricity group, the motor with the battery is fixed in the tail vaulting pole, the tail vaulting pole is hollow combined material structure.
Upper rotor driving system actuating mechanism includes four motors, 1# motor, 2# motor, 3# motor and 4# motor, lower floor's rotor driving system actuating mechanism includes four motors, 5# motor, 6# motor, 7# motor and 8# motor, 1# motor with coaxial arrangement about 5# motor, and mutual independence, 2# motor with coaxial arrangement about 6# motor, and mutual independence, 3# motor with coaxial arrangement about 7# motor, and mutual independence, 4# motor with coaxial arrangement about 8# motor, and mutual independence.
1# motor with 5# motor drives the rotor that corresponds and carries out the opposite direction rotation with anticlockwise and clockwise respectively, 2# motor with 6# motor drives the rotor that corresponds and carries out the opposite direction rotation with anticlockwise and clockwise respectively, 3# motor with 7# motor drives the rotor that corresponds and carries out the opposite direction rotation with anticlockwise and clockwise respectively, 4# motor with 8# motor drives the rotor that corresponds and carries out the opposite direction rotation with anticlockwise and clockwise respectively.
The tail vaulting pole is equipped with two, right tail vaulting pole and left tail vaulting pole, right side tail vaulting pole with the upper and lower two-layer of left side tail vaulting pole respectively is equipped with two motors, right side tail vaulting pole with left side tail vaulting pole is located the left and right sides of fuselage, right side tail vaulting pole with the connection horizontal fin of the afterbody of left side tail vaulting pole, the wing in the intermediate junction, the right outer wing in the right side of well wing is connected, the left outer wing in the left side of well wing is connected, a plurality of electricity are organized ESC in the tail vaulting pole, every coaxial two other 2 electricity of installing of motor are organized ESC.
The upper rotor power system actuating mechanism and the lower rotor power system actuating mechanism play the same role, and the two motors at the corresponding positions of the upper layer and the lower layer have the same role.
The tail stay bar is internally provided with a plurality of power batteries, a power battery, a 1# battery, a 2# battery, a 3# battery and a 4# battery are installed beside each coaxial two motors, the 1# battery and the 2# battery are connected in series to form a battery pack, an ESC (electronic control system) is electrically adjusted to supply power to the upper rotor power system actuating mechanism independently, the 3# battery and the 4# battery are connected in series to form the battery pack, and the ESC is electrically adjusted to supply power to the lower rotor power system actuating mechanism independently.
The battery is installed in the front and back part of tail vaulting pole, the middle wing is connected the mid portion of tail vaulting pole, the battery is in the position distributes around the middle wing.
The layout method of the redundant vertical starting power system of the composite vertical take-off and landing aircraft is characterized in that: the method comprises the following steps:
the method comprises the following steps that firstly, the number of vertical take-off and landing power rotors is increased, the power and the current of a single motor are reduced, and meanwhile, the power redundancy and the execution mechanism redundancy of the system are increased, so that an upper-layer and lower-layer independent power supply and operation system is formed;
and secondly, setting the left and right power arms of the combined type VTOL aircraft into an empty structure, and respectively installing the electric regulating assembly ESC (17), the motor and the battery at the front and rear parts of the left and right power arms of the combined type VTOL aircraft.
The invention has the beneficial effects that:
1. for the combined type vertical take-off and landing aircraft with the take-off weight within the range of 50-180kg, the number of the power rotors for vertical take-off and landing is increased, the power and the current of a single motor are reduced, the power redundancy and the execution mechanism redundancy of the system are increased, the existing market shelf products are utilized to the maximum extent, and the manufacturing cost is reduced; the overall dimension of the aircraft is reduced, and the transportation and the storage are convenient; the redundancy safety is improved, and the accident rate is reduced; the space of load and fuel is not occupied, the utilization rate of the space of the aircraft body is improved, and the flight time is improved;
2. the electric regulating group ESC, the motor and the battery are not arranged in the aircraft body, the battery group does not occupy the space of internal load and fuel oil of the aircraft body, and the utilization rate of the internal space of the aircraft body and the flight time are improved;
3. the invention provides a redundant vertical take-off and landing aircraft with a redundant vertical starting power system scheme, which comprises an actuating mechanism redundancy and a power supply redundancy, wherein the aircraft can keep stable posture in a multi-rotor mode unless two motors on a single shaft break down simultaneously;
4. the battery packs are respectively arranged at the front and rear parts of the left and right tail support rods of the combined type vertical take-off and landing aircraft, the tail support rods are of hollow structures, and the motor body, the electric adjusting assembly and the battery packs can be arranged in the tail support rods, so that the rotary inertia of the aircraft in the rolling direction is increased, and the realization of the balance control of the rolling attitude of the flight controller is facilitated
5. The invention forms a four-axis eight-paddle layout form, increases the number of vertical take-off and landing power rotors, reduces the power and current of a single motor, and simultaneously increases the power supply redundancy and the execution mechanism redundancy of the system.
Drawings
FIG. 1 is a schematic diagram of a redundant vertical takeoff and landing aircraft vertical power system of the present invention.
FIG. 2 is a schematic diagram of the electrical circuit configuration of the redundant vertical takeoff and landing aircraft power system of the present invention.
In the figure: the electric control system comprises a motor 1, a motor 2, a motor 3, a motor 4, a motor 5, a motor 6, a motor 7, a motor 8, a rotor 9, a right tail stay 10, a left tail stay 11, a fuselage 12, a horizontal tail wing 13, a middle wing 14, a right outer wing 15, a left outer wing 16, an electric control ESC17, a battery 18, a battery 2, a battery 3 and a battery 4, wherein the motor 1 is a motor 2, the motor 4 is a motor 4, the motor 5 is a motor 6, the motor 7 is a motor 7, the motor 8 is a motor 8, the rotor 9 is a rotor wing, the tail stay right is a tail stay left, the horizontal tail wing 13 is a horizontal tail wing 14.
Detailed Description
The invention is further described below with reference to fig. 1-2, without limiting the scope of the invention.
In which like parts are designated by like reference numerals. It is noted that the terms "front", "back", "left", "right", "upper" and "lower" used in the following description refer to directions in the drawings, the terms "inner" and "outer" refer to directions toward and away from, respectively, the geometric center of a particular component, and the drawings are in greatly simplified form and employ non-precise ratios, merely for the purpose of facilitating and distinctly aiding in the description of the embodiments of the present invention.
In the following description, for purposes of clarity, not all features of an actual implementation are described, well-known functions or constructions are not described in detail since they would obscure the invention with unnecessary detail, it being understood that in the development of any actual embodiment, numerous implementation details must be set forth in order to achieve the developer's specific goals, such as compliance with system-related and business-related constraints, changing from one implementation to another, and it being recognized that such development effort might be complex and time consuming, but would nevertheless be a routine undertaking for those of ordinary skill in the art.
A redundant vertical starting power system of a combined type vertical take-off and landing aircraft comprises an execution mechanism redundant system and a power supply redundant system, wherein the execution mechanism redundant system and the power supply redundant system are both arranged on a tail stay bar of the aircraft, the execution mechanism redundant system comprises an upper rotor power system execution mechanism and a lower rotor power system execution mechanism, the upper rotor power system execution mechanism and the lower rotor power system execution mechanism both comprise a plurality of motors, each motor is connected with a corresponding rotor 9, the upper rotor power system execution mechanism and the lower rotor power system execution mechanism play the same role, the two motors at the corresponding positions of the upper layer and the lower layer have the same role, the rotation directions of two adjacent motors of the upper rotor power system execution mechanism are opposite, and the rotation directions of two adjacent motors of the lower rotor power system execution mechanism are also opposite, this constitutes an actuator redundancy solution for the redundant vertical takeoff and landing aircraft power system of the hybrid vertical takeoff and landing aircraft.
Electronic grouping ESC17, motors and batteries are fixed at a location outside of airframe 12.
The electric regulating assembly ESC17, the motor and the battery are fixed in a tail stay bar, the tail stay bar is a hollow composite material structural member, and the cross section of the tail stay bar is oval.
Upper rotor driving system actuating mechanism includes four motors, 1# motor 1, 2# motor 2, 3# motor 3 and 4# motor 4, lower floor's rotor driving system actuating mechanism includes four motors, 5# motor 5, 6# motor 6, 7# motor 7 and 8# motor 8, coaxial arrangement about 1# motor 1 and 5# motor 5, and mutual independence, coaxial arrangement about 2# motor 2 and 6# motor 6, and mutual independence, coaxial arrangement about 3# motor 3 and 7# motor 7, and mutual independence, coaxial arrangement about 4# motor 4 and 8# motor 8, and mutual independence.
1 # motor 1 and 5# motor 5 drive the rotor 9 that corresponds and carry out the opposite direction rotation with anticlockwise and clockwise respectively, 2# motor 2 and 6# motor 6 drive the rotor 9 that corresponds and carry out the opposite direction rotation with anticlockwise and clockwise respectively, 3# motor 3 and 7# motor 7 drive the rotor 9 that corresponds and carry out the opposite direction rotation with anticlockwise and clockwise respectively, 4 # motor 4 and 8# motor 8 drive the rotor 9 that corresponds and carry out the opposite direction rotation with anticlockwise and clockwise respectively.
Two tail vaulting poles are equipped with, right tail vaulting pole 10 and left tail vaulting pole 11, the upper and lower two-layer of right tail vaulting pole 10 and left tail vaulting pole 11 respectively is equipped with two motors, right tail vaulting pole 10 and left tail vaulting pole 11 are located the left and right sides of fuselage 12, the connection horizontal fin 13 of afterbody of right tail vaulting pole 10 and left tail vaulting pole 11, wing 14 in the intermediate junction, right outer wing 15 is connected on the right side of middle wing 14, left outer wing 16 is connected in the left side of middle wing 14, a plurality of power battery are equipped with in the tail vaulting pole, power battery of installation is all by two coaxial motors of every, 1# battery 18, 2 # battery 19, 3 # battery 20, 4# battery 21.
A plurality of electric regulation groups ESC17 are arranged in the tail stay bar, 2 electric regulation groups ESC17 are arranged beside each two coaxial motors, direct current voltage provided by the electric regulation groups ESC17 battery is converted into three-phase voltage (U, V, W) which is respectively input to the brushless direct current motor, and the driving motor rotates according to the designated rotating speed.
The 1# battery 18 and the 2# battery 19 are connected in series to form a 12S (48V) battery pack, the independent upper-layer rotor power system actuating mechanism is simultaneously supplied with power through an electric regulation group ESC17, the 3# battery 20 and the 4# battery 21 are connected in series to form the 12S (48V) battery pack, and the independent lower-layer rotor power system actuating mechanism is simultaneously supplied with power through an electric regulation group ESC17, so that a power supply redundancy scheme of a redundant vertical starting power system of the combined type vertical take-off and landing aircraft is formed.
The batteries are arranged at the front part and the rear part of the tail stay bar, the middle wing 14 is connected at the middle part of the tail stay bar, and the batteries are distributed at the front position and the rear position of the middle wing 14.
A layout method of a redundant vertical starting power system of a composite vertical take-off and landing aircraft comprises the following processes:
the method comprises the following steps that firstly, the number of vertical take-off and landing power rotors is increased, the power and the current of a single motor are reduced, and meanwhile, the power redundancy and the execution mechanism redundancy of the system are increased, so that an upper-layer and lower-layer independent power supply and operation system is formed;
and secondly, setting the left and right power arms of the combined type VTOL aircraft into an empty structure, and respectively installing the electric regulating assembly ESC (17), the motor and the battery at the front and rear parts of the left and right power arms of the combined type VTOL aircraft.
Although the invention has been described and illustrated in some detail, it should be understood that various modifications may be made to the described embodiments or equivalents may be substituted, as will be apparent to those skilled in the art, without departing from the spirit of the invention.
Claims (10)
1. The redundant vertical starting power system of the combined type vertical take-off and landing aircraft is characterized in that: it includes redundant system of actuating mechanism and the redundant system of power supply, the redundant system of actuating mechanism and the redundant system of power supply all set up on the tail vaulting pole of aircraft, the redundant system of actuating mechanism includes upper rotor driving system actuating mechanism and lower floor's rotor driving system actuating mechanism, upper rotor driving system actuating mechanism with lower floor's rotor driving system actuating mechanism all includes a plurality of motors, all installs rotor (9) that correspond on every motor, upper rotor driving system actuating mechanism's two double-phase neighbour's motor direction of rotation is opposite, lower floor's rotor driving system actuating mechanism's two double-phase neighbour's motor direction of rotation is also opposite.
2. The redundant vertical take-off and landing aircraft vertical launch power system of claim 1, wherein: the electric regulating group ESC (17), the motor and the battery are fixed at positions outside the machine body (12).
3. The redundant vertical take-off and landing aircraft vertical launch power system of claim 2, wherein: the electric regulating assembly ESC (17), the motor and the battery are fixed in a tail stay bar, and the tail stay bar is a hollow composite material structural member.
4. The redundant vertical take-off and landing aircraft vertical launch power system of claim 1, wherein: upper rotor driving system actuating mechanism includes four motors, 1# motor (1), 2# motor (2), 3# motor (3) and 4# motor (4), lower floor's rotor driving system actuating mechanism includes four motors, 5# motor (5), 6# motor (6), 7# motor (7) and 8# motor (8), 1# motor (1) with coaxial arrangement about 5# motor (5), and mutually independent, 2# motor (2) with coaxial arrangement about 6# motor (6), and mutually independent, 3# motor (3) with coaxial arrangement about 7# motor (7), and mutually independent, 4# motor (4) with coaxial arrangement about 8# motor (8), and mutually independent.
5. The redundant vertical take-off and landing aircraft vertical launch power system of claim 4, wherein: 1# motor (1) and 5# motor (5) drive rotor (9) that corresponds and carry out the opposite direction rotation with anticlockwise and clockwise respectively, 2# motor (2) with 6# motor (6) drive rotor (9) that corresponds and carry out the opposite direction rotation with anticlockwise and clockwise respectively, 3# motor (3) with 7# motor (7) drive rotor (9) that corresponds and carry out the opposite direction rotation with anticlockwise and clockwise respectively, 4# motor (4) with 8# motor (8) drive rotor (9) that corresponds and carry out the opposite direction rotation with anticlockwise and clockwise respectively.
6. The redundant vertical take-off and landing aircraft vertical launch power system of claim 4, wherein: the tail vaulting pole is equipped with two, right tail vaulting pole (10) and left tail vaulting pole (11), right side tail vaulting pole (10) with the upper and lower two-layer of left side tail vaulting pole (11) respectively is equipped with two motors, right side tail vaulting pole (10) with left side tail vaulting pole (11) are located fuselage (12) the left and right sides, right side tail vaulting pole (10) with the connection horizontal fin (13) of the afterbody of left side tail vaulting pole (11), wing (14) in the intermediate junction, right outer wing (15) are connected on the right side of well wing (14), left outer wing (16) are connected in the left side of well wing (14), a plurality of electricity are organized ESC (17) are equipped with in the tail vaulting pole, and 2 electricity are organized ESC (17) are all installed to every two coaxial motors other.
7. The redundant vertical take-off and landing aircraft vertical launch power system of claim 4, wherein: the upper rotor power system actuating mechanism and the lower rotor power system actuating mechanism play the same role, and the two motors at the corresponding positions of the upper layer and the lower layer have the same role.
8. The redundant vertical take-off and landing aircraft vertical launch power system of claim 6, wherein: a plurality of power batteries are installed in the tail stay bar, and power battery of installation, 1# battery (18), 2# battery (19), 3# battery (20), 4# battery (21) are all had to every two coaxial motors other, 1# battery (18) with form the group battery after 2# battery (19) establish ties, give independence simultaneously through electricity accent group ESC (17) upper rotor driving system actuating mechanism supplies power, 3# battery (20) with form the group battery after 4# battery (21) establish ties, give independence simultaneously through electricity accent group ESC (17) lower floor rotor driving system actuating mechanism supplies power.
9. The redundant vertical take-off and landing aircraft vertical launch power system of claim 8, wherein: the battery is installed in the front and back part of tail vaulting pole, middle wing (14) are connected the mid portion of tail vaulting pole, the battery is in middle wing (14) front and back position distributes.
10. The layout method of the redundant vertical starting power system of the composite vertical take-off and landing aircraft is characterized in that: the method comprises the following steps:
the method comprises the following steps that firstly, the number of vertical take-off and landing power rotors is increased, the power and the current of a single motor are reduced, and meanwhile, the power redundancy and the execution mechanism redundancy of the system are increased, so that an upper-layer and lower-layer independent power supply and operation system is formed;
and secondly, setting the left and right power arms of the combined type VTOL aircraft into an empty structure, and respectively installing the electric regulating assembly ESC (17), the motor and the battery at the front and rear parts of the left and right power arms of the combined type VTOL aircraft.
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| CN113002784A (en) * | 2021-04-06 | 2021-06-22 | 广东汇天航空航天科技有限公司 | Power device of electric manned aircraft and electric manned aircraft |
| US12017764B2 (en) | 2020-10-27 | 2024-06-25 | Wisk Aero Llc | VTOL aircraft fan tilting mechanisms and arrangements |
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| CN109515705A (en) * | 2018-11-20 | 2019-03-26 | 西安爱生无人机技术有限公司 | A kind of unmanned plane of VTOL |
| AU2019101129A4 (en) * | 2019-09-30 | 2019-10-31 | Liu, Bingwei MR | Coaxial Reverse Rotary Wing Mini UAV |
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Application publication date: 20200728 |