CN111645879B - Ampere force driven flight method and aircraft - Google Patents
Ampere force driven flight method and aircraft Download PDFInfo
- Publication number
- CN111645879B CN111645879B CN202010360024.3A CN202010360024A CN111645879B CN 111645879 B CN111645879 B CN 111645879B CN 202010360024 A CN202010360024 A CN 202010360024A CN 111645879 B CN111645879 B CN 111645879B
- Authority
- CN
- China
- Prior art keywords
- conductor
- aircraft
- ampere
- force
- voltage
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000000034 method Methods 0.000 title claims abstract description 20
- 239000004020 conductor Substances 0.000 claims abstract description 225
- 230000001133 acceleration Effects 0.000 claims abstract description 29
- 238000009413 insulation Methods 0.000 claims abstract 2
- 230000001105 regulatory effect Effects 0.000 claims description 19
- 230000006698 induction Effects 0.000 claims description 14
- 239000000463 material Substances 0.000 claims description 8
- 230000001681 protective effect Effects 0.000 claims description 7
- 230000001276 controlling effect Effects 0.000 claims description 5
- 238000001514 detection method Methods 0.000 claims description 4
- 230000033228 biological regulation Effects 0.000 claims description 3
- 239000000615 nonconductor Substances 0.000 claims description 3
- 239000000446 fuel Substances 0.000 abstract 1
- 230000000694 effects Effects 0.000 description 4
- 230000033001 locomotion Effects 0.000 description 4
- 238000004146 energy storage Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 238000012795 verification Methods 0.000 description 3
- 238000004364 calculation method Methods 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 230000002708 enhancing effect Effects 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 241000282414 Homo sapiens Species 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 239000012050 conventional carrier Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 235000008216 herbs Nutrition 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000012811 non-conductive material Substances 0.000 description 1
- 230000008520 organization Effects 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/40—Arrangements or adaptations of propulsion systems
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Control Of Vehicles With Linear Motors And Vehicles That Are Magnetically Levitated (AREA)
Abstract
The application provides an ampere force driven flight method and an aircraft. Three conductors which are mutually orthogonally arranged are arranged in the aircraft, and the three conductors and the aircraft body are designed into an integrated insulation mode. The flight method comprises the following steps: acquiring a preset acceleration of the aircraft; calculating the ampere force borne by the aircraft according to the preset acceleration; acquiring the magnetic field directions and the magnetic field strengths of the positions of the three conductors; the ampere force is decomposed into three ampere component forces which are respectively consistent with the stress directions of the three conductors, and the current strength and the current direction in the three conductors are calculated according to the magnetic field strength, the magnetic field direction and the three ampere component forces; and supplying power to the three conductors according to the current direction and the current intensity. The ampere force driving flight method and the aircraft solve the problems that a traditional carrier is large in size, limited in fuel, inflexible in space flight and the like.
Description
Technical Field
The invention relates to the technical field of space flight verification, in particular to an ampere force driven flight method and an aircraft.
Background
At present, the main approaches of human beings to enter space are a launch vehicle and a space shuttle, and after the space shuttle in the United states exits from a historical stage, the only space vehicle is the launch vehicle. These conventional vehicles have a large volume, low flexibility of space flight and limited flight speed, and need to carry a large amount of propellant energy, which limits the application of the spacecraft.
In view of this, there is a need to verify that an ampere-force driven aircraft can fly quickly and flexibly in space.
Disclosure of Invention
Aiming at the technical problems in the related art, the invention provides an ampere force driven flight method and an aircraft, which verify the advantages of flexible flight, multi-degree-of-freedom steering and the like under the condition of enough magnetic field intensity.
One aspect of the present invention provides an ampere-force driven flight method for aircraft flight, wherein three conductors are arranged orthogonally to each other in an aircraft, and the three conductors are designed to be insulated integrally with an aircraft fuselage, the method comprising: acquiring a preset acceleration of the aircraft; calculating the ampere force borne by the aircraft according to the preset acceleration; acquiring the direction and the strength of a magnetic field at the position of a conductor; the ampere force is decomposed into three ampere component forces which are respectively consistent with the stress directions of the three conductors, and the current intensity and direction in the three conductors are calculated according to the direction and intensity of the magnetic field and the three ampere component forces; and supplying power to the three conductors according to the current direction and the current intensity.
In one embodiment, calculating the ampere force applied to the aircraft from the preset acceleration comprises: and calculating the ampere force according to the current external force borne by the aircraft and the mass of the aircraft.
In one embodiment, obtaining the magnetic field direction and strength at the location of the conductor comprises: and detecting the magnetic field of the conductor at the position in real time.
In one embodiment, calculating the current intensities in the three conductors according to the magnetic field direction and intensity and the three ampere force components is specifically:
by function F1 ═ BI1L1*sinθ1,F2＝BI2L2*sinθ2，F3＝BI3L3*sinθ3
To obtain I1＝F1/BL1*sinθ1；
I2＝F2/BL2*sinθ2；
I3＝F3/B＝L3*sinθ3
The strength of a magnetic induction line at the position of the aircraft is B, the length of a first conductor is L1, the length of a second conductor is L2, the length of a third conductor is L3, the ampere component force required to be provided by the first conductor is F1, the ampere component force required to be provided by the second conductor is F2, the ampere component force required to be provided by the third conductor is F3, and theta 1, theta 2 and theta 3 are respectively an included angle between the current direction in the first conductor and the magnetic induction line direction, an included angle between the current direction in the second conductor and the magnetic induction line direction and an included angle between the current direction in the third conductor and the magnetic induction line direction; judging the current directions in the three conductors according to the magnetic field intensity, the magnetic field direction and the three ampere component forces as follows: and judging the current direction in the corresponding conductor according to the direction of each ampere component and the direction of the magnetic field and according to the right-hand rule.
The invention provides an ampere force driven aircraft, which comprises an aircraft body, a conductor bearing piece arranged in the aircraft body, a controller, a voltage regulating commutator and a power distribution system, wherein the conductor bearing piece is arranged in the aircraft body; the conductor force bearing part at least comprises a first conductor, a second conductor and a third conductor which are arranged in an orthogonal mode, the voltage-regulating commutator comprises a first voltage-regulating commutator, a second voltage-regulating commutator and a third voltage-regulating commutator, two ends of the first conductor are electrically connected to the first voltage-regulating commutator, two ends of the second conductor are electrically connected to the second voltage-regulating commutator, and two ends of the third conductor are electrically connected to the third voltage-regulating commutator; the controller is respectively connected with the first voltage-regulating commutator, the second voltage-regulating commutator and the third voltage-regulating commutator and is used for controlling each voltage-regulating commutator to perform voltage regulation, positive and negative commutation and switching operation; the controller is electrically connected with the power distribution system to control the power distribution system to start and stop supplying power to each voltage regulating commutator; the controller is used for acquiring a preset acceleration of the ampere force driven aircraft and calculating the ampere force of the aircraft according to the preset acceleration; the controller is also used for acquiring the direction and the strength of a magnetic field at the position of the conductor, and decomposing the ampere force into three ampere component forces which are respectively consistent with the stress directions of the three conductors; the controller calculates the current intensity and direction in the three conductors according to the magnetic field intensity and direction in the space where the conductors are located and the three ampere component forces, and controls the voltage-regulating commutators to supply power to the three conductors according to the current intensity and direction in each conductor.
In one embodiment, the first voltage regulator is internally provided with a current reversing circuit and a transformer, wherein the current reversing circuit is used for changing the current flowing direction in the first conductor, and the transformer is used for regulating the voltage applied to the two ends of the first conductor; a current reversing circuit and a transformer are arranged in the second voltage regulator, wherein the current reversing circuit is used for changing the current flowing direction in the second conductor, and the transformer is used for regulating the voltage applied to two ends of the second conductor; the inside current commutation circuit and the transformer of being equipped with of third voltage regulator, wherein current commutation circuit is used for changing the electric current flow direction in the third conductor, the transformer is used for adjusting and is applyed the voltage at third conductor both ends.
In one embodiment, the first conductor is integrally insulated from the aircraft fuselage in a design to simultaneously transmit an ampere force to the aircraft when subjected to the ampere force; the second conductor is integrally insulated from the aircraft fuselage to simultaneously transmit an ampere force to the aircraft when subjected to the ampere force; the third conductor is integrally insulated from the aircraft fuselage to simultaneously transmit an ampere force to the aircraft when subjected to the ampere force.
In one embodiment, the first conductor, the second conductor and the third conductor are respectively provided with a protective material on the outer side, and the protective material is a non-conductor.
In one embodiment, the ampere-force driven aircraft further comprises a detector, wherein the detector is used for detecting the strength and direction information of the magnetic induction lines at the spatial position of the aircraft and sending a detection signal to the controller.
In one embodiment, the controller is further configured to obtain instantaneous magnetic field direction and strength at the position of the conductor in real time, calculate instantaneous current strength and direction in the first conductor, the second conductor and the third conductor in real time according to extra applied ampere force required by the aircraft, and control the voltage regulating commutator to supply expected instantaneous voltage to the three conductors.
The ampere force driving flight method and the aircraft can realize flexible motion of the aircraft in space through the conductor force bearing piece which is integrally arranged, and overcome the defects of large volume and inflexible flight of the conventional carrier.
Those skilled in the art will recognize additional features and advantages upon reading the detailed description, and upon viewing the accompanying drawings.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
FIG. 1 is a flow chart of an Ampere force driven flight method according to the present invention.
FIG. 2 is a schematic diagram of a control module of an ampere-force driven aircraft, according to an embodiment of the present invention.
Detailed Description
The technical scheme of the invention is further explained by the specific implementation mode in combination with the attached drawings. Spatially relative terms such as "below," "… below," "lower," "above," "… above," "upper," and the like are used for convenience in describing the positioning of one element relative to a second element and are intended to encompass different orientations of the device in addition to different orientations than those illustrated in the figures. Further, for example, the phrase "one element is over/under another element" may mean that the two elements are in direct contact, or that there is another element between the two elements. Furthermore, terms such as "first", "second", and the like, are also used to describe various elements, regions, sections, etc. and should not be taken as limiting. Like terms refer to like elements throughout the description.
In view of weak magnetic field intensity in earth and planet, if the current intensity is not big enough and the length of the stressed conductor is not big, the aircraft can not be supported to fly by the ampere force generated by the natural space magnetic field, and the flight test verification can be carried out in the artificial space magnetic field. For example, the united states generates magnetic fields of up to 100 tesla in the experimental environment, which corresponds to 200 ten thousand times the strength of the earth's magnetic field. On the one hand, such laboratory ampere-force driven aircraft can be used for verification of the technology required for the space flight of the aircraft; on the other hand, the method can be used as a science popularization experience in a laboratory.
In addition, the aircraft may be provided with magnetic field concentration devices for enhancing the external magnetic field thereof (the individual conductors of the present application may be placed in the magnetic field enhanced by these magnetic field concentration devices), and the magnetic field concentration devices are provided with external magnetic field paths for enhancing the external magnetic field, and the external magnetic field paths include an enhancement path, as described in the patent application No. 201910118550.6. It should be noted that the intensity of the earth's magnetic field is weak, and in order to generate a larger thrust, the magnetic field at the position of the conductor needs to be enhanced so as to achieve the purpose of propelling the aircraft to fly.
It should be noted that if the superconducting technology can be applied in engineering, that is, the superconducting material can realize superconductivity in a state of normal temperature or near normal temperature, the aircraft of the present application can depart from the environment of the artificial magnetic field, and to a certain extent, space flight depending on the planetary magnetic field is realized, and these expected products formed by the technology of the present application are all within the protection scope of the present application.
One aspect of the present invention provides an ampere-force driven flight method for an aircraft, wherein three conductors are arranged orthogonally to each other in the aircraft, and the three conductors are designed to be insulated integrally with the aircraft fuselage. Referring to fig. 1, the method includes:
s1, acquiring the preset acceleration of the aircraft;
s2, calculating the ampere force applied to the aircraft according to the preset acceleration;
s3, acquiring the direction and the strength of the magnetic field at the position of the conductor;
s4, the ampere force is decomposed into three ampere component forces which are respectively consistent with the stress of three conductors, and the current intensity and direction in the three conductors are calculated according to the direction and intensity of the magnetic field and the three ampere component forces;
s5 provides power to the three conductors according to the current direction and current intensity.
According to the ampere force driving flight method provided by the embodiment of the invention, three bearing conductors are arranged on the aircraft, so that the ampere force required by the aircraft can be decomposed in the stress directions of the three conductors, the current intensity and the current direction in the conductors are determined, and the aircraft can fly by means of the ampere force.
It should be noted that, typically, an aircraft first determines the target location for its intended flight. On the basis of this, an optimal flight path can be selected by the control computer of the aircraft by calculation and the flight acceleration can be determined from the flight path. Furthermore, the aircraft may also receive ground flight commands, i.e. transmit desired flight target positions and flight acceleration commands to the aircraft, or these commands may also be input by the pilot via an input system of the control computer. During the flight, the acceleration of the aircraft can be changed in real time, and at the moment, a controller (or a control computer) is needed to calculate the instantaneous acceleration of the aircraft in real time and adjust the intensity and direction of the current in the conductor in real time so as to meet the instantaneous acceleration requirement of the aircraft.
In addition, after determining the extra ampere force applied to the aircraft space, obviously, the ampere force can be decomposed into the resultant force of three directions in the three-dimensional coordinate system, and the three directions can be consistent with the force application directions of the three conductors, so that the stress of the aircraft in all directions can be ensured to be decomposed in the three directions by setting the position relationship of the three conductors. That is, after the force direction of the aircraft is determined, the component force directions in three directions can also be determined. If the resultant force to which the aircraft is subjected is a certain value, by adjusting the magnitudes of the three directional component forces, a force can be obtained which corresponds to the direction and magnitude of the resultant force.
In the invention, the three conductors are orthogonally arranged in a manner similar to a three-dimensional coordinate system, so that the extra applied ampere force required by the aircraft is better decomposed in the direction of the ampere force applied to the three conductors, and therefore, the stress of the three conductors can be more conveniently calculated.
In one embodiment, calculating the applied ampere force to the aircraft from the preset acceleration comprises: and calculating the ampere force according to the current external force borne by the aircraft and the mass of the aircraft. If the aircraft is in a certain position in space and the resultant force is zero, the additional applied ampere force is directly F ma. If the aircraft is subjected to an action force different from zero, it needs to be subjected to a force analysis, and the resultant force F to which the aircraft is subjectedCombination of Chinese herbs＝ma。
In one embodiment, obtaining the magnetic field direction and the magnetic field strength at the location of the aircraft comprises: and detecting the magnetic field of the space where the conductor is located in real time, wherein the magnetic field comprises the strength and the direction of the magnetic field, and the direction and the strength of the magnetic field are used for calculating the stress magnitude and the stress direction of the electrified conductor.
In one embodiment, calculating the current intensities in the three conductors according to the magnetic field direction and intensity and the three ampere force components is specifically:
by function F1 ═ BI1L1*sinθ1,F2＝BI2L2*sinθ2，F3＝BI3L3*sinθ3
To obtain I1＝F1/BL1*sinθ1；
I2＝F2/BL2*sinθ2；
I3＝F3/B＝L3*sinθ3
The strength of the magnetic induction line at the position where the aircraft is located is B, the length of the first conductor is L1, the length of the second conductor is L2, the length of the third conductor is L3, the ampere component force required to be provided by the first conductor is F1, the ampere component force required to be provided by the second conductor is F2, the ampere component force required to be provided by the third conductor is F3, and theta 1, theta 2 and theta 3 are respectively an included angle between the current direction in the first conductor and the magnetic induction line direction, an included angle between the current direction in the second conductor and the magnetic induction line direction, and an included angle between the current direction in the third conductor and the magnetic induction line direction.
It should be noted that, if all three conductors are straight strip-shaped, the stress can be directly calculated according to the above formula. If the three conductors are only regular strips under a certain length, the accumulation of the regular strips after being stressed can be calculated respectively, and at the moment, the conductors of each microscopic section also need to be orthogonal to each other so as to ensure that the ampere force of the aircraft can be easily decomposed into the ampere component force applied to each conductor.
In addition, the specific judgment of the current directions in the three conductors according to the magnetic field strength, the magnetic field direction and the three ampere force components is as follows: and judging the current direction in the corresponding conductor according to the direction of each ampere component and the direction of the magnetic field and according to the right-hand rule.
Another aspect of the invention provides an ampere-force driven aircraft including an aircraft fuselage, a conductor carrier disposed within the aircraft fuselage, a controller 10, a voltage regulating commutator, and a power distribution system 50.
The conductor force bearing part at least comprises a first conductor, a second conductor and a third conductor which are arranged in an orthogonal mode, the voltage-regulating commutator comprises a first voltage-regulating commutator 20, a second voltage-regulating commutator 30 and a third voltage-regulating commutator 40, two ends of the first conductor are electrically connected to the first voltage-regulating commutator 20, two ends of the second conductor are electrically connected to the second voltage-regulating commutator 30, and two ends of the third conductor are electrically connected to the third voltage-regulating commutator 40.
The controller is respectively connected with the first voltage-regulating commutator 20, the second voltage-regulating commutator 30 and the third voltage-regulating commutator 40 and is used for controlling each voltage-regulating commutator to execute voltage regulation, positive and negative commutation and switching operation; the controller 10 is electrically connected to the power distribution system 50 to control the start and stop of the power supply of the power distribution system 50 to each voltage-regulating commutator.
The controller 10 is configured to obtain a preset acceleration of the aircraft driven by the ampere force, and calculate the ampere force of the aircraft according to the preset acceleration. The controller 10 is further configured to obtain the direction and strength of the magnetic field of the conductor, and decompose the ampere force into three ampere force components respectively consistent with the stressed directions of the three conductors. The controller 10 calculates the current intensity and direction in the three conductors according to the magnetic field intensity and direction in the space where the aircraft is located and the three ampere component forces, and controls each voltage-regulating commutator to supply power to the three conductors according to the current intensity and direction required in each conductor.
The ampere force driven aircraft can realize the flight in a test magnetic field space by adjusting the current intensity and direction in the bearing conductor, and improves the space maneuvering flexibility of the aircraft.
In one embodiment, the first voltage regulator 20 is internally provided with a current commutation circuit for changing the direction of current flow in the first conductor and a transformer for regulating the voltage applied across the first conductor. The second voltage regulator 20 is provided therein with a current commutation circuit for the current flowing in the second conductor and a transformer for regulating the voltage applied across the second conductor. The third voltage regulator 30 is provided therein with a current commutation circuit for changing the direction of current flowing in the third conductor, and a transformer for regulating the voltage applied to both ends of the third conductor. The aircraft can easily realize the adjustment of the magnitude and the direction of the ampere force borne by the three conductors by independently controlling the magnitude and the direction of the current.
In this embodiment, the ampere force element is a conductor, and to avoid the power distribution system or the conductor from being burned out due to excessive current, a variable resistive element may be connected in series between the voltage regulator and the conductor, wherein the organization of the resistive element may be continuously adjusted from 0 to 10 ohms with an adjustment accuracy of at least 0.001 ohms. By adjusting the resistance precisely, in particular to a minimum, extremely high currents can be generated in the conductor, so that high ampere forces are obtained.
In one embodiment, the first conductor is integrally insulated from the aircraft fuselage in a design to simultaneously transmit an ampere force to the aircraft when subjected to the ampere force; the second conductor is integrally insulated from the aircraft fuselage to simultaneously transmit an ampere force to the aircraft when subjected to the ampere force; the third conductor is integrally insulated from the aircraft fuselage to simultaneously transmit an ampere force to the aircraft when subjected to the ampere force. According to the ampere driving aircraft provided by the embodiment of the invention, the conductor and the aircraft body are integrally designed, so that the effect of carrying and transmitting ampere force by the conductor can be improved, and the reliability of the aircraft is improved.
In one embodiment, the first conductor, the second conductor and the third conductor are respectively provided with a protective material on the outer side, and the protective material is a non-conductor. The protective material can prevent the conductor from being damaged by mutual extrusion with the aircraft fuselage when the conductor is subjected to ampere force, and the durability of the aircraft is improved.
In one embodiment, power distribution system 50 includes a solar powered assembly. The solar powered component may be a photovoltaic film or solar panel, which may be disposed inside the aircraft fuselage. In use, for example, the aircraft may first be forced to rest or move slowly and then be opened after the solar panels have been extended from the fuselage. After solar charging is completed, the solar energy collector can be retracted and the outer side of the solar energy collector is flushed with the aircraft body, so that the damage to a solar energy assembly caused by high-speed movement of the aircraft can be avoided on the one hand, and the influence on the pneumatic performance of the aircraft caused by excessive structures on the outer side of the aircraft body is avoided on the other hand.
It should be noted that the power distribution system 50 may also include an energy storage device for storing electrical energy to electrically connect the energy storage device to the conductor when power is required to be supplied to the conductor. Likewise, the disconnection of the energy storage from the conductor can also be controlled by the controller.
In one embodiment, the ampere-force driven vehicle further comprises a detector for detecting the strength and direction information of the magnetic induction line at the position of the conductor and sending the detection signal to the controller. Since in some embodiments the aircraft is also equipped with a magnetic field enhancement assembly, the detector detects the composite magnetic field strength at the location where the force-bearing conductor is actually located. Typically, several conductor bearers can be arranged in close proximity, and it can be assumed that the magnetic field strength in these areas is approximately equal. Of course, if the magnetic field intensity difference of several conductors is large, several magnetic field intensity detectors corresponding to these conductors can be set up respectively, in this case, the stress of each conductor is calculated according to the magnetic field corresponding to it respectively, so as to improve the accuracy of magnetic field detection and current calculation.
For a single conductor bearing part, the magnetic fields are obviously different, for example, for a long-strip-shaped conductor bearing part, a plurality of magnetic field detectors can be arranged at intervals along the length direction of the conductor bearing part, so that the current in the conductor can be reversely calculated through the ampere component force applied to the conductor bearing part, and the accuracy of calculating the current in the conductor is improved.
In one embodiment, the controller 10 is further configured to obtain the direction and strength of the magnetic field at the position of the conductor in real time, calculate the current strength and direction in the first conductor, the second conductor and the third conductor in real time according to the expected ampere force of the aircraft, and control the voltage-regulating commutator to supply expected instantaneous voltage to the three conductors respectively in real time.
As can be seen by those skilled in the art, the three conductors and the fuselage of the present application may be integrated to extend a variety of deformation extensions, including two or more sets of such devices symmetrically disposed within or outside the aircraft, thereby providing access to, symmetrically applying forces to, and further improving flexibility and stability of starting, steering, and attitude adjustment of the aircraft.
As an alternative embodiment, the ampere-force driven vehicle of the present application may be a disc-type structure, and a plurality of conductors are provided in a circumferential direction of the disc-type structure. The conductors may be arranged at different angles along the circumferential direction of the disc, for example, the number of circular arcs in the circumferential direction of the disc may vary from 20 degrees to 180 degrees. The conductors with the same length or different lengths can be arranged on the outer surface of the disc in all directions, so that the conductors with different lengths and different arrangement positions generate acting forces in different directions when the aircraft is in the same magnetic field.
The ends of these conductors extend, for example, into the interior of a disk-type aircraft, where the two ends of the conductors are electrically connected to and controlled by a voltage-regulating commutator by means of wires to effect a change in the current intensity and direction. Each conductor can be controlled individually to improve redundancy and avoid damage to the aircraft caused by damage to individual voltage regulating commutators or conductors.
As previously described, the controller may calculate its additional amperage based on the acceleration of the aircraft. Meanwhile, the detector sends signals related to the direction and strength of the magnetic field at the position of each conductor to the controller in real time, so that the controller can find several conductors which can most easily obtain the extra ampere force from the relation between the ampere force component received by the conductors and the total ampere force, and then the voltage regulating commutator is controlled to supply expected voltage to the several conductors. For example, according to the ampere force of the aircraft, the controller may first determine the force-bearing direction of each conductor in combination with the magnetic field direction, compare the force-bearing direction with the ampere force of the aircraft, and find out the conductor that is most likely to synthesize the ampere force, so as to control the voltage-regulating commutator to energize the conductors.
In this application, it is obvious that the larger the number of conductors provided by the aircraft, the wider the area of the disk covering the aircraft, the more ways it can obtain the ampere force of the aircraft after being electrified, and the more suitable conductors can be selected by the controller as the electrified objects.
It should be noted that the selection principle of the most suitable conductors includes: the direction of resultant force is the best consistent with the direction of ampere force applied to the aircraft; the task quantity needing to be adjusted and reversed is minimum; and the acceleration generated by the resultant force is closest to the preset acceleration, etc. The controller can calculate the stress directions of all the conductors on the premise of acquiring the magnetic fields of all the conductors, compare the stress directions with the ampere resultant force required by the aircraft, and comprehensively calculate the optimal selection for obtaining the ampere force, so that the aircraft can be accelerated quickly with the minimum energy consumption.
It will be appreciated that in this embodiment, if the conductors are properly located on the aircraft, the aircraft may be powered on to achieve various motions of the aircraft such as spatial rest, inversion, steering, etc., as desired for the motion.
In the aircraft of the embodiment of the application, in order to increase the stressed length of the conductors and improve the ampere force to which the conductors are subjected, each conductor can be in a wound coil structure, and the outer side of each coil is wrapped by a non-conductive material.
The above embodiments may be combined with each other with corresponding technical effects.
The ampere-driven aircraft of the application can (is not limited to) be a small-sized space aircraft, an unmanned aerial vehicle and the like.
The above-described embodiments of the present invention may be combined with each other with corresponding technical effects.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (10)
1. An ampere force drive flight method is used for aircraft flight, wherein a plurality of conductors are arranged in the aircraft, each conductor is respectively provided with a voltage regulating commutator, and the plurality of conductors and an aircraft fuselage are designed into an integrated insulation mode, and the ampere force drive flight method is characterized by comprising the following steps:
determining a preset flying target position of the aircraft;
acquiring a preset acceleration of the aircraft according to the preset flying target position;
calculating the ampere force borne by the aircraft according to the preset acceleration;
acquiring the direction and the strength of a magnetic field at the position of a conductor;
comparing the ampere component force applied to each conductor of the ampere force, and selecting a plurality of conductors which can most easily obtain the ampere force; wherein the conductor selection principle comprises: the direction of resultant force is the best consistent with the direction of the ampere force borne by the aircraft, the quantity of tasks needing to be adjusted and reversed is the least, and the acceleration generated by the resultant force is the closest to the preset acceleration;
the conductors are powered at the desired current.
2. The ampere-force driven flight method of claim 1,
calculating the applied ampere force to the aircraft from the preset acceleration comprises:
and calculating the ampere force according to the current external force borne by the aircraft and the mass of the aircraft.
3. The ampere-force driven flight method according to claim 1, wherein obtaining the magnetic field direction strength at the location of the conductor comprises:
and detecting the magnetic field of the conductor at the position in real time.
4. The ampere-force driven flight method of claim 1,
calculating current intensities in the three conductors according to the direction and the strength of the magnetic field and the three ampere force components specifically comprises the following steps:
by function F1= BI1L1*sinθ1,F2=BI2L2*sinθ2，F3=BI3L3*sinθ3
To obtain I1= F1/B L1*sinθ1；
I2= F2/ BL2*sinθ2;
I3= F3/B=L3*sinθ3
The strength of a magnetic induction line at the position of the aircraft is B, the length of a first conductor is L1, the length of a second conductor is L2, the length of a third conductor is L3, the ampere component force required to be provided by the first conductor is F1, the ampere component force required to be provided by the second conductor is F2, the ampere component force required to be provided by the third conductor is F3, and theta 1, theta 2 and theta 3 are respectively an included angle between the current direction in the first conductor and the magnetic induction line direction, an included angle between the current direction in the second conductor and the magnetic induction line direction and an included angle between the current direction in the third conductor and the magnetic induction line direction;
judging the current directions in the three conductors according to the magnetic field intensity, the magnetic field direction and the three ampere component forces as follows:
and judging the current direction in the corresponding conductor according to the direction of each ampere component and the direction of the magnetic field and according to the right-hand rule.
5. An ampere force driven aircraft is characterized by comprising an aircraft body, a conductor force bearing piece arranged in the aircraft body, a controller, a voltage regulating commutator, a detector and a power distribution system;
the conductor force bearing part at least comprises a first conductor, a second conductor and a third conductor which are arranged in an orthogonal mode, the voltage-regulating commutator comprises a first voltage-regulating commutator, a second voltage-regulating commutator and a third voltage-regulating commutator, two ends of the first conductor are electrically connected to the first voltage-regulating commutator, two ends of the second conductor are electrically connected to the second voltage-regulating commutator, and two ends of the third conductor are electrically connected to the third voltage-regulating commutator;
the controller is respectively connected with the first voltage-regulating commutator, the second voltage-regulating commutator and the third voltage-regulating commutator and is used for controlling each voltage-regulating commutator to perform voltage regulation, positive and negative commutation and switching operation; the controller is electrically connected with the power distribution system to control the power distribution system to start and stop supplying power to each voltage regulating commutator;
the controller is used for acquiring the acceleration of the ampere force driven aircraft and calculating the ampere force of the aircraft according to the acceleration;
the detector is used for sending signals related to the direction and the strength of the magnetic field at the position of each conductor to the controller in real time, so that the controller is used for finding out the conductors which can obtain the ampere force most easily from the relation between the ampere force component received by the conductors and the total ampere force, and then controlling the voltage-regulating commutator to supply expected voltage to the conductors; the controller selects the corresponding conductor to supply the expected current according to the principle that the direction of resultant force of the conductors is the best consistent with the direction of the ampere force borne by the aircraft, the task quantity needing to be adjusted and reversed is the least, and the acceleration generated by the resultant force is the closest to the preset acceleration.
6. The Ampere-force driven aerial vehicle of claim 5, wherein,
a current reversing circuit and a transformer are arranged in the first voltage-regulating commutator, wherein the current reversing circuit is used for changing the current flow direction in the first conductor, and the transformer is used for regulating the voltage applied to two ends of the first conductor;
a current reversing circuit and a transformer are arranged in the second voltage-regulating commutator, wherein the current reversing circuit is used for changing the current flow direction in the second conductor, and the transformer is used for regulating the voltage applied to two ends of the second conductor;
and a current reversing circuit and a transformer are arranged in the third voltage regulating commutator, wherein the current reversing circuit is used for changing the current flowing direction in the third conductor, and the transformer is used for regulating and applying the voltage at two ends of the third conductor.
7. The Ampere-force driven aerial vehicle of claim 5, wherein,
the first conductor is integrally insulated from the aircraft fuselage to simultaneously transmit an ampere force to the aircraft when subjected to the ampere force;
the second conductor is integrally insulated from the aircraft fuselage to simultaneously transmit an ampere force to the aircraft when subjected to the ampere force;
the third conductor is integrally insulated from the aircraft fuselage to simultaneously transmit an ampere force to the aircraft when subjected to the ampere force.
8. An ampere-force driven vehicle according to claim 7, wherein the first, second and third conductors are each provided with a protective material on the outside thereof, the protective material being a non-conductor.
9. An ampere-force driven vehicle as claimed in claim 5, further comprising a detector for detecting information on the direction and strength of the magnetic field at the location of the conductor and sending a detection signal to the controller.
10. An ampere-force driven aircraft according to any one of claims 5 to 9, wherein the controller is further configured to obtain in real time the instantaneous magnetic field direction and strength at the location of the conductors, and to calculate in real time the instantaneous current strength and direction in the first, second and third conductors and to control the regulating commutator to supply the desired instantaneous voltage to the three conductors, in dependence on the required ampere force of the aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010360024.3A CN111645879B (en) | 2020-04-30 | 2020-04-30 | Ampere force driven flight method and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010360024.3A CN111645879B (en) | 2020-04-30 | 2020-04-30 | Ampere force driven flight method and aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111645879A CN111645879A (en) | 2020-09-11 |
| CN111645879B true CN111645879B (en) | 2021-07-23 |
Family
ID=72351983
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010360024.3A Active CN111645879B (en) | 2020-04-30 | 2020-04-30 | Ampere force driven flight method and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111645879B (en) |
Family Cites Families (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102030113B (en) * | 2009-10-01 | 2013-04-24 | 徐跃 | Strong electromagnetic propulsion device |
| US10486835B2 (en) * | 2013-03-12 | 2019-11-26 | William R. Crowe | Centrifugal force amplification method and system for generating vehicle lift |
| CN106184822A (en) * | 2016-04-18 | 2016-12-07 | 刘德智 | Utilize the propulsion mode of Ampere force |
| CN107016897A (en) * | 2017-05-02 | 2017-08-04 | 北京信息科技大学 | A kind of electromagnetic power Multi-axis aircraft |
| CN108033009A (en) * | 2017-12-08 | 2018-05-15 | 燕胜 | A kind of magnetomotive inspection aircraft based on magnetic field |
| CN108900063A (en) * | 2018-01-10 | 2018-11-27 | 深圳市丹明科技有限公司 | The braking and/or power generator in propeller, magnetic field in magnetic field |
| CN108490972A (en) * | 2018-03-21 | 2018-09-04 | 深圳臻迪信息技术有限公司 | Flight control method, system and the electronic equipment of aircraft |
| CN109573106B (en) * | 2018-10-30 | 2021-10-26 | 南京航空航天大学 | Superconducting magnetic propulsion device for spacecraft |
| CN110304244A (en) * | 2019-06-26 | 2019-10-08 | 深圳市道通智能航空技术有限公司 | Flight control method, device, vert rotor aircraft and medium |
-
2020
- 2020-04-30 CN CN202010360024.3A patent/CN111645879B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN111645879A (en) | 2020-09-11 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8167234B1 (en) | Insect-like micro air vehicle having perching, energy scavenging, crawling, and offensive payload capabilities | |
| JP6672260B2 (en) | Spacecraft propulsion system and method | |
| Envall et al. | E-sail test payload of ESTCube-1 nanosatellite | |
| US10965125B2 (en) | Simultaneous bidirectional power usage of generator power feeders | |
| CN111645879B (en) | Ampere force driven flight method and aircraft | |
| CN102862687A (en) | Magnetic propulsion device for low orbit spacecraft | |
| KR101089118B1 (en) | Minesweeping Device | |
| Fujii et al. | Sounding rocket experiment of bare electrodynamic tether system | |
| CN111907732B (en) | Space verification aircraft | |
| US11267589B2 (en) | Drag-based propellant-less small satellite attitude orbit and de-orbit control system | |
| CN214190169U (en) | Space verification aircraft for magnetic field environment | |
| US20160083119A1 (en) | Thrust Augmentation Systems | |
| Niccolai | Optimal deep-space heliocentric transfers with an electric sail and an electric thruster | |
| US5752381A (en) | Method and apparatus for vectoring thrust employing electrodes generating voltages greater than the dielectric breakdown voltage | |
| Snyder et al. | Peak power tracking and multi-thruster control in direct drive systems | |
| Bonifazi et al. | TSS core equipment: I.—Electrodynamic package and rationale for system electrodynamic analysis | |
| US6089509A (en) | Spacecraft attitude control using electrical power subsystem | |
| US9824807B2 (en) | Magnetic thrust generation system | |
| RU2092401C1 (en) | Method of electrodynamic action with magnetoplasma near-planet medium and electrodynamic cable system for realization of this method | |
| Gilchrist et al. | Picosat/Femtosatellite Electrodynamic Tether Propulsion | |
| Hennick | Subsystem development and flight testing of an electroaerodynamic UAV | |
| US20080111655A1 (en) | Magnetic flotation device | |
| WO2022264177A1 (en) | Electromagnetic propulsion system for spacecraft movement without the emission of reaction mass | |
| Karagöz et al. | Turkish First Indigenous 100V Satellite Power Subsystem | |
| Nizin et al. | Power system design concepts of a reusable launch vehicle-technology demonstrator (RLV-TD) |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |