CN111907732A - Space verification aircraft - Google Patents
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- CN111907732A CN111907732A CN202010721336.2A CN202010721336A CN111907732A CN 111907732 A CN111907732 A CN 111907732A CN 202010721336 A CN202010721336 A CN 202010721336A CN 111907732 A CN111907732 A CN 111907732A
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
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- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
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- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
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- 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
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/428—Power distribution and management
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- 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
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Abstract
The application provides a space verification aircraft, include: a housing defining an aircraft exterior and an interior space; the force-bearing conductors are arranged on the shell along different directions and used for providing ampere force for the aircraft after being electrified in a magnetic field environment; the voltage-regulating commutator is used for electrifying the force-bearing conductors and changing the current flow direction in the conductors; the controller is used for calculating the current intensity and direction of the bearing conductor to be selected and the bearing conductor according to the current power supply state of the bearing conductors, and controlling the voltage-regulating commutator to provide the expected current intensity and current direction for the selected bearing conductor; and the distributor is electrically connected with the voltage-regulating commutator and the controller and is used for supplying power to the voltage-regulating commutator under the control of the controller. The application provides an aircraft is verified in space can realize the nimble motion of aircraft under the high-intensity magnetic field environment, and then verifies the correlation technique of electromagnetic flight.
Description
The application is a divisional application of an invention patent with the application number of 202010359508.6, which is filed on 30.4.2020 and is named as "a space verification aircraft".
Technical Field
The invention relates to the technical field of space flight verification, in particular to a space verification 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 the above, there is a need to verify an ampere-force driven space verification aircraft capable of flying fast and flexibly in space to verify electromagnetic flight technology.
Disclosure of Invention
Aiming at the technical problems in the related art, the invention provides an ampere force driven space verification aircraft, which verifies the advantages of flexible flight, multi-degree-of-freedom steering and the like under the condition of enough magnetic field intensity.
The invention provides a space verification aircraft, which comprises: a housing defining an aircraft exterior and an interior space; the force-bearing conductors are arranged on the shell along different directions and used for providing ampere force for the aircraft after being electrified in a magnetic field environment; the voltage regulating commutator is arranged in the inner space and used for electrifying the force bearing conductors and changing the current intensity and the current direction in the conductors; the controller is used for calculating extra ampere force required by the aircraft according to the acceleration of the aircraft, calculating the current intensity and direction of the bearing conductor to be selected and the bearing conductor according to the current power supply state of the bearing conductors, and controlling the voltage-regulating commutator to provide the expected current intensity and current direction for the selected bearing conductor; and the distributor is electrically connected with the voltage-regulating commutator and the controller and is used for supplying power to the voltage-regulating commutator under the control of the controller.
In one embodiment, each of the force-bearing conductors is connected with a voltage-regulating commutator, so that each voltage-regulating commutator independently controls the corresponding force-bearing conductor.
In one embodiment, the force bearing conductors at least comprise two groups of force application conductors, the two groups of force application conductors are symmetrically arranged relative to the aircraft, and each group of force application conductors at least comprises three force bearing conductors which are arranged orthogonally to each other.
In one embodiment, the parts of the multiple force-bearing conductors between the two ends are integrally formed with the shell, and the two ends of the multiple force-bearing conductors penetrate through the shell and then are connected with the corresponding voltage-regulating commutators.
In one embodiment, two ends of the force bearing conductors penetrate through the shell and then are connected with corresponding voltage regulating commutators through leads.
In one embodiment, the space verification vehicle further comprises a magnetic field detector for sending a magnetic field strength signal to the controller.
In one embodiment, the magnetic field detectors include a plurality of magnetic field detectors positioned to match the location of each messenger.
In one embodiment, the controller acquires the power supply state of each force-bearing conductor and the instantaneous magnetic field intensity of the position of the force-bearing conductor in real time, and adjusts the power supply state of the force-bearing conductor in real time according to the instantaneous ampere force additionally applied to the aircraft.
In one embodiment, the controller selects the corresponding force-bearing conductor and the pressure-regulating commutator to act according to the current stress of each force-bearing conductor and the additionally applied ampere force required by the current stress of each force-bearing conductor on the basis of the principle that the action change of the pressure-regulating commutator is least and the consistency between the pressure-regulating commutator and the ampere force after the action of the pressure-regulating commutator is optimal.
In one embodiment, the aircraft is a disc-shaped aircraft, the outer side of the disc-shaped aircraft comprises a plurality of force-bearing conductors arranged along the circumferential direction and a plurality of force-bearing conductors arranged along the direction perpendicular to the circumferential direction, and each force-bearing conductor is integrally formed with the disc-shaped aircraft.
According to the space verification aircraft provided by the embodiment of the invention, the power supply state of each bearing conductor can be changed by the controller according to the acceleration required by the aircraft, so that the ampere force borne by the conductor bearing pieces integrally arranged on the aircraft shell is changed, and the expected flight of the aircraft in a high-intensity magnetic field space is realized.
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 a space-verifying aircraft in accordance with an embodiment of the 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/B L1*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 a space verification aircraft, which comprises an aircraft fuselage, a conductor bearing member arranged in 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 space verification aircraft can realize the flight in the test magnetic field space by adjusting the current intensity and the 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 space verification vehicle further comprises a detector for detecting the strength and direction information of the magnetic induction lines at the positions of the conductors and sending the detection signals 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.
Yet another aspect of the present invention provides another space verification aircraft. The space validation aircraft may include:
an outer shell defining an aircraft exterior and an interior space.
The force-bearing conductors are arranged on the shell along different directions and used for providing ampere force for the aircraft after being electrified in a magnetic field environment. For example, the force-bearing conductors at least comprise two groups of force application conductors, and the two groups of force application conductors are symmetrically arranged relative to the aircraft, so that ampere force can be symmetrically applied to the aircraft, and the force bearing stability of the aircraft is improved. For example, each set of force-exerting conductors comprises at least three force-bearing conductors arranged orthogonally to each other, so that the required additional ampere resultant force of the aircraft can be easily resolved into the force-bearing directions of the three conductors.
And the voltage regulating commutator is arranged in the inner space and used for electrifying the bearing conductors and changing the current intensity and the flow direction in the conductors. For example, each of the multiple force-bearing conductors is respectively connected with a pressure-regulating commutator, so that each pressure-regulating commutator independently controls the corresponding force-bearing conductor, and the influence on the normal work of the aircraft caused by the damage of the pressure-regulating commutator when the pressure-regulating commutator is uniformly controlled by a single pressure-regulating commutator is avoided.
And the controller is used for calculating extra ampere force required by the aircraft according to the acceleration of the aircraft, calculating the current intensity and direction of the bearing conductor to be selected and the bearing conductor according to the current power supply state of the bearing conductors, and controlling the voltage-regulating commutator to provide expected current intensity and current direction for the selected bearing conductor.
And the distributor is electrically connected with the voltage-regulating commutator and the controller and is used for supplying power to the voltage-regulating commutator under the control of the controller.
The space verification aircraft can calculate the power supply state required by each bearing conductor in real time through the controller, so that the power distributor and the voltage regulator are controlled to adjust the current intensity and direction of the corresponding conductors, and the aircraft can obtain required acceleration.
In one embodiment, for example, two ends of a plurality of force bearing conductors penetrate through the shell and are connected with corresponding voltage regulating commutators through leads.
In one embodiment, the space verification vehicle further comprises a magnetic field detector for sending a magnetic field strength signal to the controller. Further, if the geomagnetic fields at the positions of the force-bearing conductors are different, the magnetic field detectors can comprise a plurality of magnetic field detectors which are matched with the positions of the force-bearing conductors, so that the accuracy of calculating the ampere force according to the magnetic field intensity is improved.
In one embodiment, the controller can acquire the power supply state of each bearing conductor and the instantaneous magnetic field intensity of the position of the bearing conductor in real time, and adjust the power supply state of the bearing conductor in real time according to the instantaneous ampere force additionally borne by the aircraft. For example, the controller can select the corresponding force-bearing conductor and the voltage-regulating commutator to act according to the current stress of each force-bearing conductor and the additionally applied ampere force required by the current stress of each force-bearing conductor on the basis of the principle that the action change of the voltage-regulating commutator is the least and the consistency of the voltage-regulating commutator after the action and the ampere force is the best.
In this embodiment, for example, it may be defined that the angle between the resultant ampere force direction of the force-bearing conductor and the required ampere force direction does not exceed 1 degree, which is a precondition for the aircraft to achieve the required acceleration, and on this basis, the pressure regulating amplitude and the commutation times of the pressure regulating commutator connected with the force-bearing conductor are uniformly distributed on the aircraft as the selection basis. Specifically, on the premise that the direction of the ampere resultant force of the bearing conductor is satisfied, the bearing conductor is more uniform, the frequency of pressure regulation is less, and the pressure regulation amplitude is smaller, so that the bearing conductor is more likely to be used as the selected bearing conductor. Considering that the stable stress of the aircraft is an important factor influencing the service life of the aircraft and the conductor, the uniformity of the force-bearing conductor is taken as a first priority, the frequency of voltage regulation is taken as a second priority, and the amplitude of voltage regulation is taken as a third priority, namely, the high priority is taken as a target firstly. The aircraft of this embodiment through setting up different priorities, can improve the stationarity of aircraft flight, increases the life-span of pressure regulating commutator, load conductor.
It should be noted that the catenary conductor and the aircraft skin need to be insulated from each other, i.e., the current only flows in the catenary conductor.
The commutation of the voltage-regulating commutator can be realized in various ways only by a simple circuit, which can be seen in the prior art of changing the positive and negative poles of elements, and is not described in detail here. Similarly, there are various ways to change the magnitude of the current, such as connecting a sliding rheostat in series.
As described above, as an alternative embodiment, the space verification aircraft of the present application may be a disk-type structure, and a plurality of conductors are provided in the circumferential direction of the disk-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.
As previously mentioned, the selection principle of the most suitable conductor may include: 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. ControlThe system can calculate the stress directions of all conductors under the premise of acquiring the magnetic fields of all conductors, and then the stress directions are calculated The direction of the force applied is compared with the resultant ampere force required by the aircraft, and the optimal choice for obtaining the ampere force is comprehensively calculated, so that Acceleration of the aircraft is achieved rapidly with minimal 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 space verification aircraft of the application can be (is not limited to) 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 (9)
1. A space validation aircraft, comprising:
a housing defining an aircraft exterior and an interior space;
the force-bearing conductors are arranged on the shell along different directions and used for providing ampere force for the aircraft after being electrified in a magnetic field environment; the conductor bearing part at least comprises a first conductor, a second conductor and a third conductor which are arranged orthogonally to each other;
the voltage-regulating commutator is arranged in the inner space and used for electrifying the force-bearing conductors and changing the current intensity and the current direction in the conductors, 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;
a magnetic field detector for sending a magnetic field strength signal to the controller;
the controller is respectively and electrically connected with the first voltage-regulating commutator, the second voltage-regulating commutator and the third voltage-regulating commutator, and is used for calculating extra ampere force required by the aircraft according to the acceleration and magnetic field intensity signals of the aircraft, calculating the current intensity and direction of the bearing conductor to be selected and the bearing conductor according to the current power supply state of the three bearing conductors, and controlling the voltage-regulating commutator to provide the expected current intensity and current direction to the selected bearing conductor; the controller calculates the principle that the bearing conductors to be selected are uniformly distributed on the aircraft, the pressure regulating frequency is low and the pressure regulating amplitude is small, the bearing conductors are uniformly distributed on the aircraft as a first priority, the pressure regulating frequency is low as a second priority, and the pressure regulating amplitude is low as a third priority, so that in the process of selecting the bearing conductors, the bearing conductors meeting the second priority are selected only under the condition that the requirement of the first priority on the uniform distribution of the bearing conductors is met, and the bearing conductors meeting the third priority are selected only under the condition that the requirement of the first priority and the requirement of the second priority are met simultaneously;
the distributor is electrically connected with the voltage-regulating commutator and the controller, and is used for supplying power to the voltage-regulating commutator under the control of the controller, and the power distribution system comprises a solar power supply assembly which is arranged inside the space verification aircraft and outside the space verification aircraft and flushed with the aircraft body.
2. The space-validation aircraft according to claim 1, wherein each of the plurality of messenger wires is connected to a voltage-regulating commutator such that each voltage-regulating commutator independently controls a corresponding messenger wire.
3. The space-validation aircraft according to claim 1, wherein the plurality of messenger conductors comprises at least two sets of force conductors, the two sets of force conductors being symmetrically disposed with respect to the aircraft, and each set of force conductors comprising at least three messenger conductors disposed orthogonally to one another.
4. The space verification aircraft of claim 1, wherein the portions of the messenger conductors between the two ends are integrally formed with the outer shell, and the two ends of the messenger conductors are connected to corresponding voltage-regulating commutators after passing through the outer shell.
5. The space validation aircraft of claim 4, wherein both ends of the plurality of force-bearing conductors are connected with the corresponding voltage-regulating commutators through wires after passing through the outer shell.
6. The space-validating vehicle of claim 1, wherein the magnetic field detectors include a plurality of magnetic field detectors positioned to match the locations of the messenger conductors.
7. The space verification aircraft of claim 1, wherein the controller obtains the power supply state of each force-bearing conductor and the instantaneous magnetic field strength of the position of the force-bearing conductor in real time, and adjusts the power supply state of the force-bearing conductor in real time according to the instantaneous ampere force additionally applied by the aircraft.
8. The space verification aircraft of claim 7, wherein the controller selects the corresponding force-bearing conductor and controls the pressure-regulating commutator to act according to the current force of each force-bearing conductor and the additionally applied ampere force required by the current force, on the basis that the action change of the pressure-regulating commutator is minimum, and the consistency between the pressure-regulating commutator and the ampere force after the action is optimal.
9. The space verification aircraft of claim 1, wherein the aircraft is a disk-shaped aircraft, the outer side of the disk-shaped aircraft comprises a plurality of force-bearing conductors arranged along a circumferential direction and a plurality of force-bearing conductors arranged along a direction perpendicular to the circumferential direction, and each force-bearing conductor is integrally formed with the disk-shaped aircraft.
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| CN111252267A (en) | 2020-06-09 |
| CN111907732B (en) | 2021-09-14 |
| CN111252267B (en) | 2021-02-19 |
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