CN116395131B - Ultra-high speed aircraft lean flow drag reduction method and system - Google Patents
Ultra-high speed aircraft lean flow drag reduction method and system Download PDFInfo
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- CN116395131B CN116395131B CN202310257648.6A CN202310257648A CN116395131B CN 116395131 B CN116395131 B CN 116395131B CN 202310257648 A CN202310257648 A CN 202310257648A CN 116395131 B CN116395131 B CN 116395131B
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- 238000005086 pumping Methods 0.000 claims abstract description 26
- 230000007935 neutral effect Effects 0.000 claims abstract description 18
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- 239000007789 gas Substances 0.000 description 59
- 125000004429 atom Chemical group 0.000 description 18
- 230000009471 action Effects 0.000 description 6
- 125000004433 nitrogen atom Chemical group N* 0.000 description 5
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
- B64C23/005—Influencing air flow over aircraft surfaces, not otherwise provided for by other means not covered by groups B64C23/02 - B64C23/08, e.g. by electric charges, magnetic panels, piezoelectric elements, static charges or ultrasounds
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
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Abstract
The invention discloses a method and a system for reducing drag of rarefaction flow of an ultra-high-speed aircraft, wherein the method comprises the following steps: laser pumping is carried out on the incoming gas before the incoming gas collides with the incoming wall surface of the ultra-high speed aircraft, so that the neutral atomic energy state of the incoming gas falls on a single energy state which cannot be transited; and a non-uniform magnetic field is formed on the peripheral side of the incoming flow wall surface of the ultra-high speed aircraft, so that neutral atoms of incoming flow gas are repelled by the non-uniform magnetic field due to own intrinsic magnetic moment, the normal speed of the incoming flow gas relative to the incoming flow wall surface is reduced, and the drag reduction effect on the ultra-high speed aircraft is achieved. According to the characteristics of the thin gas, the invention provides a method for pumping the incoming gas by laser and forming magnetic gradient force by adopting a non-uniform strong magnetic field, thereby reducing the normal speed of the incoming gas relative to the incoming wall surface, reducing the resistance and solving the problem that the friction resistance of the high overspeed aircraft in the air space of the thin gas increases synchronously with the increase of the flying speed.
Description
Technical Field
The invention belongs to the field of ultra-high speed flight, and particularly relates to a method and a system for reducing drag of thin flow of an ultra-high speed aircraft.
Background
In the airspace 50-200 km from the ground, the ultra-high speed aircraft has a large development space. However, the air pressure in the airspace environment is lower, the air is rarefied, and along with the remarkable improvement of the flight speed, such as an ultra-high speed aircraft with the speed exceeding 2km/s, the collision frequency between the rarefied air and the wall surface of the aircraft is remarkably increased, and for the ultra-high speed aircraft with long voyage, the friction resistance brought by the collision frequency is unfavorable for the ultra-high speed flight.
Existing high-speed flight drag reduction techniques are primarily directed to conventional flight environments. Conventional flight drag reduction techniques such as gas discharge to change the viscosity of air, jet flow to change the flow field of the boundary layer, etc. are designed for dense atmospheres.
In air-rarefied airspace (e.g., near space), the air around the aircraft is very rarefied, and drag is mainly due to momentum transfer caused by random collisions of gas molecules with the walls.
Conventional drag reduction methods such as discharging are difficult to achieve under such lean gas conditions, and the jet may significantly increase the gas density around the aircraft, rather increasing the frequency of momentum transfer (i.e., collision frequency) of the aircraft to the outside world, which has the undesirable effect of increasing drag.
Disclosure of Invention
The invention provides a method and a system for reducing drag by rarefaction flow of an ultra-high-speed aircraft, which fully utilize the characteristics of rarefaction gas, and obviously reduce the collision between the gas and a wall surface and reduce the resistance by adopting a method of pumping the gas by laser and forming magnetic gradient force by adopting a non-uniform magnetic field so as to solve the problem that the friction resistance of the ultra-high-speed aircraft in an adjacent space increases synchronously with the increase of the flying speed.
In a first aspect of the present invention, there is provided a method of reducing drag in a lean flow of an ultra-high speed aircraft, the method comprising:
laser pumping is carried out on the incoming gas before the incoming gas collides with the incoming wall surface of the ultra-high speed aircraft, so that the neutral atomic energy state of the incoming gas falls on a single energy state which cannot be transited;
And a non-uniform magnetic field is formed on the peripheral side of the incoming flow wall surface of the ultra-high speed aircraft, so that neutral atoms of incoming flow gas are repelled by the non-uniform magnetic field due to own intrinsic magnetic moment, the normal speed of the incoming flow gas relative to the incoming flow wall surface is reduced, and the drag reduction effect on the ultra-high speed aircraft is achieved.
Further, the inhomogeneous magnetic field is a gradient magnetic field.
Further, the magnetic field range of the nonuniform magnetic field is a space within 5 molecular collision free ranges on the outer periphery side of the incoming flow wall surface of the ultra-high speed aircraft.
Further, the incoming gas is a thin gas in an airspace of 50-200 km from the ground.
Further, the method also comprises a method for calculating drag reduction efficiency of the ultra-high speed aircraft, and the method comprises the following steps of:
in a non-uniform magnetic field, neutral atoms experience a force due to their intrinsic magnetic moment:
Wherein F is magnetic gradient force, bohr magnon mu B＝9.274x 10-24J/T,gJ is a Lande factor of a certain quantum state under a fine structure, represents repeated statistical frequency of the atomic state in quantum statistics, m j is a magnetic quantum number corresponding to the quantum state, J is an angular momentum number, J is an ultra-fine energy level, Is a spatial gradient of magnetic field strength;
setting the magnetic quantum number corresponding to the only energy state incapable of transition to be settled in the neutral atomic energy state of the incoming gas in the laser pumping process, and calculating the corresponding magnetic gradient force;
If the magnetic quantum number m j =2 corresponding to the energy state incapable of transition is set, the magnetic gradient force in the flowing gas is combined with the laser pumping, and the speed of the flowing gas is used for representing the function of the local magnetic field strength:
Wherein V ⊥,0 is the initial normal velocity before the incoming flow enters the magnetic field region, V ⊥ is the normal velocity at a certain position after the incoming flow enters the magnetic field region, B is the local magnetic field strength, and M is the mass of the atoms;
The maximum stagnation normal velocity is obtained according to the function of the local magnetic field intensity and is as follows:
The atomic ratio of normal stagnation is:
In the formula, xi is the normal stagnation atomic proportion, namely drag reduction efficiency; v is an integral variable representing speed; k B =1.38e-23J/K, a physical constant; b wall is the magnetic field strength at the wall; the drag reduction efficiency ζ can be adjusted by adjusting the magnetic field strength B wall of the magnetic field.
In a second aspect of the present invention, there is also provided a system for reducing drag in a lean flow of an ultra-high speed aircraft, comprising:
The magnetic field generating device is arranged on the ultra-high speed aircraft and forms a non-uniform magnetic field on the periphery of the incoming flow wall surface of the ultra-high speed aircraft;
The laser pumping source is arranged in the ultra-high speed aircraft, generates laser and guides the laser to the wall surface of the ultra-high speed aircraft, and performs laser pumping on the incoming gas before the incoming gas collides with the incoming wall surface of the ultra-high speed aircraft.
Further, the magnetic field generating device is a permanent magnet patch.
Further, the magnetic field generating device is an excitation coil.
Further, the included angle between the laser guided to the wall surface of the ultra-high speed aircraft and the flight direction of the ultra-high speed aircraft is smaller than 90 degrees.
Compared with the prior art, the invention has the following beneficial effects:
1. According to the ultra-high speed aircraft lean flow drag reduction method provided by the invention, according to the characteristics of low gas density, low molecular collision frequency and long molecular energy state relaxation time of lean gas, the energy state of atoms in incoming gas in the vicinity of an aircraft is changed to an energy state incapable of transition by utilizing a laser light pump technology, and the effect of maintaining the energy state for a long time is realized by utilizing the characteristic of long relaxation time of the lean gas; the non-uniform magnetic field is formed on the outer periphery of the incoming flow wall surface of the aircraft, so that the atoms in the energy state in the incoming flow gas are repelled under the action of the non-uniform magnetic field, the normal speed of the incoming flow gas relative to the incoming flow wall surface is reduced, the collision with the wall surface of the aircraft and the momentum transfer are reduced, and the purpose of drag reduction in the flight process of the ultra-high speed aircraft is realized.
2. The invention provides a thin flow drag reduction system of an ultra-high speed aircraft, which provides a specific magnetic field generating device and a laser pumping source based on a thin flow drag reduction method, and a non-uniform magnetic field is formed on the periphery side of an incoming flow wall surface of the ultra-high speed aircraft through a permanent magnet patch or an excitation coil, so that neutral atoms of incoming flow gas are subjected to the repulsive action of the non-uniform magnetic field due to intrinsic magnetic moment of the neutral atoms, the normal speed of the incoming flow gas relative to the incoming flow wall surface is reduced, and the drag reduction effect on the ultra-high speed aircraft is achieved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below. It will be apparent to those skilled in the art from this disclosure that the drawings described below are merely exemplary and that other embodiments may be derived from the drawings provided without undue effort.
FIG. 1 is a schematic illustration of a magnetic gradient force repelling atoms away from a wall of a flight vessel in an embodiment of the invention;
FIG. 2 is a schematic diagram of a laser pumping process according to an embodiment of the present invention;
FIG. 3 is a graph of drag reduction efficiency versus magnetic field strength and incoming flow temperature for an embodiment of the present invention;
reference numerals in the drawings: θ is the included angle caused by the atomic thermal motion, 1 is the permanent magnet patch, 2 is the non-uniform magnetic field on the wall surface, and 3 is the wall surface of the ultra-high speed aircraft.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
According to the characteristics of the lean gas, the invention provides a method for reducing drag by lean flow of an ultra-high speed aircraft, which comprises the following steps: laser pumping is carried out on the incoming gas before the incoming gas collides with the incoming wall surface of the ultra-high speed aircraft, so that the neutral atomic energy state of the incoming gas falls on a single energy state which cannot be transited; and a non-uniform magnetic field is formed on the peripheral side of the incoming flow wall surface of the ultra-high speed aircraft, so that neutral atoms of incoming flow gas are repelled by the non-uniform magnetic field due to own intrinsic magnetic moment, the normal speed of the incoming flow gas relative to the incoming flow wall surface is reduced, and the drag reduction effect on the ultra-high speed aircraft is achieved.
The incoming gas is a thin gas in an airspace 50-200 km away from the ground, has the characteristics of low gas density, low molecular collision frequency and long molecular energy state relaxation time, changes the energy state of atoms in the incoming gas in the area near an aircraft to an energy state incapable of transition by utilizing a laser light pump technology, and realizes the effect of maintaining the energy state for a long time by utilizing the characteristic of long relaxation time of the thin gas; the non-uniform magnetic field is formed on the outer periphery of the incoming flow wall surface of the aircraft, so that the atoms in the energy state in the incoming flow gas are repelled under the action of the non-uniform magnetic field, the normal speed of the incoming flow gas relative to the incoming flow wall surface is reduced, the collision with the wall surface of the aircraft and the momentum transfer are reduced, and the drag reduction effect on the ultra-high speed aircraft is achieved.
The technical principle of the method is as follows:
In a non-uniform magnetic field, neutral atoms experience a force due to their own magnetic moment:
Wherein F is magnetic gradient force, bohr magnon (Bohr magnon) mu B＝9.274x 10-24J/T,gJ is a Lande factor of a certain quantum state under a fine structure, represents repeated statistical frequency of the atomic state in quantum statistics, m j is magnetic quantum number corresponding to the quantum state, J is angular momentum number, J is hyperfine energy level, Is a spatial gradient of magnetic field strength.
The magnetic gradient force is proportional to the magnitude of the magnetic field gradient, and the relationship can be used for generating the effect of rejecting atoms away from the wall surface. Thus, the normal velocity caused by the thermal motion of the incoming gas over a range can be counteracted by the gradient force.
Preferably, a non-uniform magnetic field can be formed on the outer periphery side of the incoming flow wall surface of the ultra-high speed aircraft, as shown in fig. 1, the magnetic field range of the non-uniform magnetic field is a space within 5 molecular collision free ranges on the outer periphery side of the incoming flow wall surface of the ultra-high speed aircraft, the non-uniform magnetic field can be a gradient magnetic field, and the generated gradient force counteracts the normal speed caused by the internal heat movement of incoming flow gas within a certain range.
Then, setting the magnetic quantum number corresponding to the only energy state incapable of transition to be settled in the neutral atomic energy state of the incoming gas in the laser pumping process, and calculating the corresponding magnetic gradient force.
Since the earth atmosphere has the highest content of N atoms, N atoms are theoretically suitable for all gases that can be pumped (the corresponding optimal m j =2 is its largest m j), pumped to create the magnetic gradient force. The optimal number of magnons can be selected according to the atomic species in the atmosphere of other stars. The effect of the gradient force is discussed below using an N atom as an example.
Since the ground state (2 s 22p4) is the vast majority of the statistical distribution, only the ground state can be considered. Fig. 2 shows the fine structure constants of the N atoms in the ground state (NIST database), where it is known that there are 3 fine structures (different angular momentum numbers) in the ground state, j=0, 1,2, respectively, and corresponding langerhans 5, 3, and 1 exist 2j+1 m j for each angular momentum number: -J, - (J-1), … …, 0, J-1, J. The atomic energy states are concentrated onto the favorable m j using optical pumping techniques. Under the action of the magnetic field, the fine structure of the atomic energy level is further subdivided, and the atomic energy level splitting, namely the Zeeman effect (Zeeman effect) occurs due to the fact that the atomic energy levels of atoms with the same angular momentum have the same energy because of the difference of m j. Under the excitation of the resonating laser, atoms transition between different energy levels. Due to the transition rule, eventually all atomic energy states fall on only one non-transition energy state (the maximum or minimum value of m j, depending on the polarization characteristics of the laser light), which is an optical pumping effect, as shown in fig. 2.
According to the principle, before the incoming gas collides with the incoming wall surface of the ultra-high speed aircraft, laser pumping is carried out on the incoming gas, so that the neutral atomic energy state of the incoming gas falls on only one energy state which cannot be transited; and then, the normal speed of the incoming gas relative to the incoming wall surface is reduced by utilizing the repulsive action of the non-uniform magnetic field on the incoming gas.
Since m j =2 is only nitrogen atom and has versatility to the atmosphere, laser pumping is used to focus all atomic energy states onto a quantum state that cannot be transitioned corresponding to a magnetic quantum number of m j of 2.
Let all atoms be pumped to m j =2, then g J =5, when the force of the magnetic field gradient is:
The potential energy Φ can thus be introduced to satisfy:
Since the collisions of particles in the thin stream are negligible and there are no collisions of particles in the field, the magnetic gradient force in the gas of the subsequent stream is pumped by the laser, and the velocity (kinetic energy) of the gas of the incoming stream is used to represent a function of the local magnetic field strength:
Where V ⊥,0 is the initial normal velocity of the incoming flow before it enters the field region, V ⊥ is the normal velocity at some point after it enters the field region, B is the local field strength, and M is the mass of the atom.
From the above analysis, the maximum stagnation normal velocity is:
From this, the atomic ratio of normal stagnation can be calculated as:
In the formula, xi is the normal stagnation atomic proportion, namely drag reduction efficiency; v is an integral variable representing speed; k B =1.38e-23J/K, a physical constant; b wall is the magnetic field strength at the wall; b is a variable representing the magnetic field strength at a certain point in space.
The drag reduction efficiency formula can be simplified as:
by formulas (6) and (7), it is possible to achieve adjustment of drag reduction efficiency by adjusting the magnetic field strength of the strong magnetic field.
After substituting Bohr's magneton and Boltzmann constant (Boltzmann constant k B), the dimensionless number isWherein the units of the magnetic field intensity (B wall) and the incoming gas temperature (T) are T and K respectively. The drag reduction efficiency is related to the magnetic field strength and the incoming flow temperature as shown in fig. 3:
typical values are:
(1) B wall/t=0.0134, drag reduction efficiency was 32.8%;
(2) B wall/t=0.149, the drag reduction efficiency is 84.2%;
(3) At B wall/t=0.446, the drag reduction efficiency was 100%.
Taking an 80km airspace as an example, the ambient gas typically has a temperature of 198K. When the maximum value of the non-uniform magnetic field intensity is 2T, B wall/T=0.010, the drag reduction ratio is about 30%, and the effect is obvious.
The invention also provides a thin flow drag reduction system of the ultra-high speed aircraft, which applies the drag reduction method, and the system comprises the following components:
The magnetic field generating device is arranged on the ultra-high speed aircraft and forms a non-uniform magnetic field on the periphery of the incoming flow wall surface of the ultra-high speed aircraft;
The laser pumping source is arranged on the ultra-high speed aircraft, generates laser and guides the laser to the wall surface of the ultra-high speed aircraft, and performs laser pumping on the incoming gas before the incoming gas collides with the incoming wall surface of the ultra-high speed aircraft.
The magnetic field range of the non-uniform magnetic field generated by the magnetic field generating device is a space within 5 molecules on the outer periphery side of the incoming flow wall surface of the ultra-high speed aircraft, and the non-uniform magnetic field is a gradient magnetic field so as to form magnetic gradient force.
In one possible embodiment, the magnetic field generating device is a permanent magnet patch, and the non-uniform magnetic field is generated to form a magnetic gradient force by installing the permanent magnet patch in the wall surface of the ultra-high speed aircraft, as shown in fig. 1. The magnets may be embedded in the aircraft wall material to a specific depth determined by the bearing capacity of the aircraft wall material.
In another possible embodiment, the magnetic field generating device is an exciting coil, and the magnetic gradient force can be formed by installing the exciting coil such as a superconducting coil on the wall surface of the ultra-high speed aircraft to generate a non-uniform magnetic field.
The laser pumping source can be installed and placed in the ultra-high speed aircraft, laser is guided to the wall of the aircraft through the light path, surrounding air is irradiated, and therefore the included angle between the direction of the laser and the flight direction of the ultra-high speed aircraft is smaller than 90 degrees, and pumping of the maximum efficiency of incoming air is achieved in the magnetic field range of the non-uniform magnetic field.
The thin flow drag reduction method and the system provided by the invention are suitable for the ultra-high speed flight of an ultra-high speed aircraft with the flight speed of more than 2km/s in the air space of thin gas, are especially suitable for the air space with low air pressure of 50-200 km from the ground, can enable neutral atoms of incoming gas to be subjected to the repulsive action of a non-uniform magnetic field due to self intrinsic magnetic moment through the non-uniform magnetic field in combination with a laser pumping technology, so as to reduce the normal speed of the incoming gas relative to the incoming wall surface, realize the drag reduction effect on the ultra-high speed aircraft, and solve the problem that the friction resistance of a high overspeed aircraft in the air space of thin gas increases synchronously with the increase of the flight speed.
The above embodiments are only exemplary embodiments of the present application and are not intended to limit the present application, the scope of which is defined by the claims. Various modifications and equivalent arrangements of this application will occur to those skilled in the art, and are intended to be within the spirit and scope of the application.
Claims (8)
1. A method of drag reduction for a lean flow of a super-high speed aircraft, the method comprising:
laser pumping is carried out on the incoming gas before the incoming gas collides with the incoming wall surface of the ultra-high speed aircraft, so that the neutral atomic energy state of the incoming gas falls on a single energy state which cannot be transited;
Forming a non-uniform magnetic field on the peripheral side of an incoming flow wall surface of the ultra-high speed aircraft, so that neutral atoms of incoming flow gas are repelled by the non-uniform magnetic field due to self intrinsic magnetic moment, the normal speed of the incoming flow gas relative to the incoming flow wall surface is reduced, and the drag reduction effect on the ultra-high speed aircraft is achieved;
the method also comprises a calculation method of drag reduction efficiency of the ultra-high speed aircraft, and the method comprises the following steps of:
in a non-uniform magnetic field, neutral atoms experience a force due to their intrinsic magnetic moment:
Wherein F is magnetic gradient force, bohr magnon mu B＝9.274x 10-24J/T,gJ is a Lande factor of a certain quantum state under a fine structure, represents repeated statistical frequency of the atomic state in quantum statistics, m j is a magnetic quantum number corresponding to the quantum state, J is an angular momentum number, J is an ultra-fine energy level, Is a spatial gradient of magnetic field strength;
setting the magnetic quantum number corresponding to the only energy state incapable of transition to be settled in the neutral atomic energy state of the incoming gas in the laser pumping process, and calculating the corresponding magnetic gradient force;
If the magnetic quantum number m j =2 corresponding to the energy state incapable of transition is set, the magnetic gradient force in the flowing gas is combined with the laser pumping, and the speed of the flowing gas is used for representing the function of the local magnetic field strength:
Wherein V ⊥,0 is the initial normal velocity before the incoming flow enters the magnetic field region, V ⊥ is the normal velocity at a certain position after the incoming flow enters the magnetic field region, B is the local magnetic field strength, and M is the mass of the atoms;
The maximum stagnation normal velocity is obtained according to the function of the local magnetic field intensity and is as follows:
The atomic ratio of normal stagnation is:
in the formula, xi is the normal stagnation atomic proportion, namely drag reduction efficiency; v is an integral variable representing speed; k B =1.38e-23J/K, a physical constant; b wall is the magnetic field strength at the wall; the drag reduction efficiency xi, u is an integral variable and T is the gas temperature near the wall surface can be adjusted by adjusting the magnetic field intensity B wall of the magnetic field.
2. A method of lean flow drag reduction according to claim 1,
The non-uniform magnetic field is a gradient magnetic field.
3. A method of lean flow drag reduction according to claim 1,
The magnetic field range of the nonuniform magnetic field is a space within 5 molecular collision free ranges on the outer periphery side of an incoming flow wall surface of the ultra-high speed aircraft.
4. A method of lean flow drag reduction according to claim 1,
The incoming gas is lean gas in the airspace 50-200 km away from the ground.
5. A ultra-high speed aircraft lean flow drag reduction system based on the lean flow drag reduction method of any of claims 1-4, comprising:
The magnetic field generating device is arranged on the ultra-high speed aircraft and forms a non-uniform magnetic field on the periphery of the incoming flow wall surface of the ultra-high speed aircraft;
The laser pumping source is arranged in the ultra-high speed aircraft, generates laser and guides the laser to the wall surface of the ultra-high speed aircraft, and performs laser pumping on the incoming gas before the incoming gas collides with the incoming wall surface of the ultra-high speed aircraft.
6. The ultra-high speed aircraft lean flow drag reducing system of claim 5,
The magnetic field generating device is a permanent magnet patch.
7. The ultra-high speed aircraft lean flow drag reducing system of claim 5,
The magnetic field generating device is an excitation coil.
8. The ultra-high speed aircraft lean flow drag reducing system of claim 5,
The included angle between the laser guided to the wall surface of the ultra-high speed aircraft and the flight direction of the ultra-high speed aircraft is smaller than 90 degrees.
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| 稀薄大气下机械展开式再入飞行器气动特性研究;包军;张鹏;尚明友;张红英;童明波;;航空计算技术(第04期);83-87 * |
| 近空间高超声速飞行器气动特性研究的若干关键问题;叶友达;《力学学报》;第50卷(第6期);1292-1310 * |
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