CN204737044U - Fast particle propulsion system of short -distance beam reaches space flight ware including this system - Google Patents
Fast particle propulsion system of short -distance beam reaches space flight ware including this system Download PDFInfo
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- CN204737044U CN204737044U CN201520280345.7U CN201520280345U CN204737044U CN 204737044 U CN204737044 U CN 204737044U CN 201520280345 U CN201520280345 U CN 201520280345U CN 204737044 U CN204737044 U CN 204737044U
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Abstract
The utility model relates to a fast particle propulsion system of short -distance beam reaches space flight ware including this system. Particularly, the utility model discloses a fast particle propulsion system of short -distance beam, propulsion system is fixed in on the major structure of space flight ware to impel the unit including the fast particle of one or more short -distance beam, the fast particle of short -distance beam impels the unit to include: impel structure, conversion of energy structure and adjust the structure. Use the device can be less the quality realize long -term acceleration and posture adjustment to the aircraft, and can greatly improve the feed rate of aircraft.
Description
Technical field
The utility model relates to aerospace field, relates to a kind of momentum effect propulsion aircraft of the dipped beam speed particle utilizing the nuclear decay of nuclear material nature to produce particularly and/or adjusts the method in aircraft orientation and the device based on the method design.
Background technology
Up to now, space craft can accelerate to and depart from the solar third cosmic velocity by the Push Technology of the mankind, and aircraft speed the fastest is at present ~ 16,000 meter per seconds, promotes further and faces very large difficulty.Trace it to its cause, be that the speed of backflushing medium is difficult to surmount 10 times of velocities of sound (~ 3 kilometers per second) because the power difficult prospect of propulsion system generation, depart from the fuel that terrestrial gravitation just needs at substantial.The rocket engine of current main-stream relies on the burning of liquid or solid fuel to form high-speed jet, produces recoil.Due to the quick consumption of used load, aircraft pick-up time is limited.So the speed that survey of deep space airship or detector generally rely on initial rocket to provide breaks away from the gravity of place celestial body, then carry out attitude and directional trim with carry-on limited power, in very long route, slide to target with almost constant speed.Arrive after target, the power still relying on similar rocket to spray such as slow down, land, again take off.Limited owing to producing the capacity weight of power, must to the meticulous planning of resource counterweight, to complete preplanned mission as much as possible.Rely on current thrust mode, namely chemistry of fuel reaction produces the mode of thrust, the space flight time is not only made very longly (to need 120-300 days from the earth at present to Mars one way, mankind's aircraft the soonest needs more than 10 years from the earth to Pluto), and capacity weight also critical constraints.For the intergalactic navigation of light-year level, current space technology is helpless.
Therefore, the mankind are exploring the promotion technology that can obtain longer-term more speed always, to shorten in the solar system and the interspace interior flight time.Some emerging propulsion systems comprise the substance sublimates Push Technology of laser triggering, and this technology relies on superlaser sublimate to produce reaction thrust, but the energy demand aircraft of laser provides.Another kind of mode is by action of high voltage in medium generating strap charged particle, then relies on electromagnetic field accelerating charged particles to produce thrust.But the material speed of the thrust that above-mentioned Push Technology can produce is difficult to more than 20,000 meter per seconds, the long duration of its propulsion system, stability and overall thrust are all still difficult to a series of rigors met in space flight.
In sum, in order to shorten the crossing time of remote aerospace survey, this area a kind ofly greatly can be improved fltting speed in the urgent need to developing and efficiently can advance novel propelling unit and the propulsion method of space craft for a long time.
Utility model content
The purpose of this utility model is to provide a kind of and greatly can improves fltting speed and efficiently can advance novel propelling unit and the propulsion method of space craft for a long time.
First aspect of the present utility model, provide a kind of dipped beam speed particle advancing system (namely for advancing the propelling unit of space craft), described propelling unit is fixed in the agent structure of described space craft, and comprise one or more dipped beam speed particle advancing unit, described dipped beam speed particle advancing unit comprises: push structure, Conversion of Energy structure and adjustment structure, wherein
Described push structure produces dipped beam speed particle, and the dipped beam speed particle that described push structure produces comprises to deviating from (going namely) dipped beam speed particle P ' of described Conversion of Energy structure direction and (namely moving ahead) dipped beam speed particle P to described Conversion of Energy structure side, and the momentum of part described dipped beam speed particle P ' is used directly as the power producing the described space craft flight of propelling;
Described Conversion of Energy structure is fixed on described space craft, for absorbing the dipped beam speed particle P that described push structure produces;
Described adjustment structure is for the dipped beam speed particle P ' that absorbs described push structure and produce thus regulate the momentum of described dipped beam speed particle P '.
In another preference, described adjustment structure is for changing the direction of propulsion of described push structure, the heading of the described dipped beam speed particle P ' that described push structure is produced is consistent with the direction of described aircraft or basically identical, thus adjusts the thrust that the fast particle P ' of described dipped beam produces.
In another preference, described adjustment structure is for regulating the momentum of described particle P '.
In another preference, described space craft is selected from lower group: satellite, spacecraft, interplanetary spacecraft.
In another preference, described space craft comprises aircraft body structure and described propelling unit.
In another preference, described space craft also comprises electric system and master control system.
In another preference, described space craft also comprises docking unit, for docked flight device agent structure and described propelling unit.
In another preference, described dipped beam speed particle advancing unit is positioned at the outside face of described space craft agent structure and symmetrical.
In another preference, described dipped beam speed particle advancing unit is positioned at the rear portion of described space craft agent structure, afterbody, middle part or its combination
In another preference, described multiple dipped beam speed particle advancing unit is connected to form thrust sail structure.
In another preference, described thrust sail structure is preferably fenestral fabric.
In another preference, described push structure is positioned at the outside face (namely towards vacuum side) of described Conversion of Energy structure, and described push structure is nuclear decay material coating.
In another preference, the thickness of described nuclear decay material coating is 1-100 μm, is preferably 3-50 μm, is more preferably 5-30 μm, is 5-15 μm best.
In another preference, described nuclear decay material coating forms primarily of nuclear decay material, with the total weight of described nuclear decay material coating, the content of described nuclear decay material is 10-99wt%, being preferably 30-99wt%, is more preferably 50-99wt%, is 60-90wt% best.
In another preference, the isotopic half life period forming the radio active element of described nuclear decay material is 0.1 second-100 years, is preferably 10 seconds-80 years, more preferably 30 seconds-10 years, 50 seconds-1 year best.
In another preference, the nuclear decay of described nuclear decay material is nature nuclear decay.
In another preference, the nuclear decay of described nuclear decay material is non-natural nuclear decay, is preferably the nuclear decay that induced with laser accelerates the half life period.
In another preference, described nuclear decay material coating can discharge dipped beam speed particle.
In another preference, speed>=3 х 10 of described dipped beam speed particle
4meter per second, preferably>=3 х 10
5meter per second, more preferably>=3 х 10
6meter per second, best>=3 х 10
7meter per second.
In another preference, the speed of described dipped beam speed particle is greater than the millesimal times light velocity.
In another preference, the speed of described dipped beam speed particle is no more than the light velocity.
In another preference, described dipped beam speed particle is massive particle, is preferably ɑ particle, neutron, proton, electronics or its combination.
In another preference, when needs accelerate described aircraft, the propulsive force Δ F > 0 along described aircraft working direction that described particle P ' produces.
In another preference, when needs slow down described aircraft, the propulsive force Δ F < 0 along described aircraft working direction that described particle P ' produces.
In another preference, when not needing the speed adjusting described aircraft, the propulsive force Δ F=0 along described aircraft working direction that described particle P ' produces.
In another preference, described Δ F is that described particle P ' is to the summation of the propulsive force that described space craft produces.
In another preference, described Conversion of Energy structure is that decay thermoelectric conversion-counter the pushing away being fixedly connected with described aircraft body structure or being flexibly connected bears structure.
In another preference, when needing the propulsive force reducing described dipped beam speed particle P ', the momentum of described adjustment structure absorption portion or whole described particle P ', thus reduce or eliminate the thrust for advancing described space craft to fly.
In another preference, described adjustment structure is positioned in described space craft agent structure.
In another preference, the direction of described adjustment structure and/or position can adjust as required.
In another preference, described adjustment structure comprises the material of particle P ' described in Absorbable rod, and preferably described material is aluminium foil.
In another preference, the transformation of energy of absorbed dipped beam speed particle P ' is be selected from the form of energy of lower group by described adjustment structure: luminous energy, mechanical energy, interior (heat) can, electric energy, nuclear energy electromagnetic energy or its combine.
In another preference, described propelling unit is also provided with one or more electromagnetic confinement device, and described electromagnetic confinement device is for retraining the heading of described dipped beam speed particle P '.
In another preference, each dipped beam speed particle advancing unit is provided with the electromagnetic confinement device described in; Or multiple dipped beam speed particle advancing unit is provided with a shared described electromagnetic confinement device; Or all dipped beams speed particle advancing unit is provided with a shared described electromagnetic confinement device.
In another preference, described electromagnetic confinement device be positioned at described push structure outside and near described push structure, and the range of movement of the magnetic field that described electromagnetic confinement device the produces particle P ' to radiation outside aircraft push structure that substantially covers that described push structure produces.
In another preference, the electric energy needed for described electromagnetic confinement device is provided by the energy source being selected from lower group: the energy of dipped beam speed particle P that described Conversion of Energy structure absorbs, the non-degenerate electric power of aircraft.
In another preference, the non-degenerate electric power of described aircraft is selected from lower group: the electric energy that solar sail is collected, nuclear power power, chemical fuel, all kinds of battery structures such as lithium cell, solar cell, fuel cell, nuclear battery or its combination.
Second aspect of the present utility model, provide a kind of method advancing space craft to fly, described method comprises the steps:
A () provides a space craft, described space craft comprises aircraft body structure and a propelling unit, and wherein said propelling unit comprises the propelling unit described in the utility model first aspect;
B () is during space flight, dipped beam speed particle advancing unit in propelling unit described in startup, the momentum of the part or all of described dipped beam speed particle P ' described push structure produced directly is used as to produce the power advancing the flight of described space craft, thus advances space craft flight.
In another preference, described method also comprises: utilize described Conversion of Energy structure to be the energy that can be utilized further by described space craft by the Conversion of Energy of described particle P.
In another preference, described method also comprises: adjustment in use structure absorbs described particle P ', thus the size of the propulsive force regulating described particle P ' to produce and/or direction.
In another preference, described method also comprises: use electromagnetic confinement device to retrain described particle P ', thus regulates size and/or the direction of propulsive force, thus described space craft is carried out to the adjustment of flying speed and/or flight orientation.
In another preference, described method is used for space environment.
In the third aspect of the present utility model, provide a kind of space craft, described space craft comprises the propelling unit described in the utility model first aspect.
Should be understood that within the scope of the utility model, above-mentioned each technical characteristic of the present utility model and can combining mutually between specifically described each technical characteristic in below (eg embodiment), thus form new or preferred technical scheme.As space is limited, tiredly no longer one by one to state at this.
Accompanying drawing explanation
Fig. 1 is the effect schematic diagram of the utility model propelling unit and space craft.
Fig. 2 is the structural representation of the utility model dipped beam speed particle advancing unit.
Fig. 3 is the momentum balance figure of the utility model dipped beam speed particle advancing unit, and solid arrow represents particle radiation signal direction, and actual capabilities are any direction, and thick arrow represents the overall heading signal of coating energetic particle beam.
Fig. 4 is the momentum balance figure that the utility model arranges the dipped beam speed particle advancing unit of electromagnetic confinement device, dotted arrow represents particle radiation signal direction, actual capabilities are any direction, but under electromagnetic confinement device, described particle P ' can be retrained, thus regulate the size and/or direction that are used for the propulsive force that propulsion aircraft advances, and then described space craft is carried out to the adjustment of flying speed and/or flight orientation; Thick arrow represents the overall heading signal of coating energetic particle beam.
Fig. 5 is the thrust sail schematic diagram that the utility model dipped beam speed particle advancing unit is formed, and arrow represents the overall heading signal of coating energetic particle beam in thrust sail structure.
Fig. 6 is the general illustration of the space craft arranging the utility model propelling unit, wherein left figure is normal flight structure, right figure is the flight structure after opening thrust sail, solid arrow represents the overall heading signal of coating energetic particle beam in thrust sail structure, and dotted line represents nuclear decay material coating.
Detailed description of the invention
The present inventor through long-term and deep research, be surprised to find that first utilize nuclear material natural decay produce particle momentum effect can directly carry out aircraft propelling and/or aircraft adjustment in direction.Particularly, the present inventor by arrange in space craft be fixed on described space craft agent structure on and comprise the propelling unit of one or more dipped beams speed particle advancing unit primarily of push structure, Conversion of Energy structure and adjustment structure composition, during space craft flight, by starting described propelling unit, the reaction thrust formed to (namely after row) dipped beam speed particle P ' deviating from described Conversion of Energy structure direction utilizing described push structure to produce can realize accelerating described space craft and/or carrying out adjustment in direction.This method can low load-carrying nuclear decay material realize to aircraft long-term, continue and stable propelling and/or adjustment in direction.Based on above-mentioned discovery, contriver completes the utility model.
Term
As used herein, term " the utility model propelling unit ", " propelling unit ", " the utility model propulsion system " or " propulsion system " are used interchangeably.
As used herein, term " the utility model push structure ", " push structure ", " the utility model dipped beam speed particle recurring structure " or " dipped beam speed particle recurring structure " is used interchangeably, all refer to the nuclear decay material coating of the outside face (namely towards vacuum side) being positioned at described Conversion of Energy structure, described nuclear decay material coating can produce dipped beam speed particle, and the dipped beam produced speed particle comprises to deviating from (going namely) dipped beam speed particle P ' of described Conversion of Energy structure direction and (namely moving ahead) dipped beam speed particle P to described Conversion of Energy structure side.
As used herein, term " the utility model Conversion of Energy structure ", " Conversion of Energy structure ", " the utility model dipped beam speed particle absorption structure " or " dipped beam speed particle absorption structure " are used interchangeably, all refer to be fixed on described space craft, and for absorbing the structure of the dipped beam speed particle P that described push structure produces.
As used herein, term " the utility model decay thermoelectric conversion-counter pushing away bears structure ", " decay thermoelectric conversion-counter pushing away bears structure ", " the utility model thermoelectric structure " or " thermoelectric structure " are used interchangeably.
As used herein, term " the utility model adjustment structure ", " adjustment structure ", " the utility model thrust adjustment structure " or " thrust adjustment structure " are used interchangeably, all refer to be positioned in described space craft agent structure, for absorbing dipped beam speed particle P ' that described push structure produces thus regulating the structure of the momentum of described dipped beam speed particle P ', or for changing the direction of propulsion of described push structure, the heading of the described dipped beam speed particle P ' that described push structure is produced is consistent with the direction of described aircraft or basically identical, thus adjust the thrust that described dipped beam speed particle P ' produces.
Theoretical calculate
Suppose that initial atomic fuel quality is M
0[units/kg], molal weight M
mol[units/kg/mol], molal quantity N
mol=6.02E23.
Initial total atom number N
0: N
0=M
0/ M
mol* N
mol
Material atom nuclear decay rule: N=N
0* 0.5^ (t/T),
Wherein T is the half life period, and t is the time, and N is the atomicity not occurring to decay.
The atomicity then decayed is N
d=N
0-N
The rate of change of decay atom: Nd (t)=dNd/dt=-N
0/ T*ln (0.5) * 0.5^ (t/T)
The dipped beam speed particle momentum P=M of alpha-decay
α* V
α, M
α=6.64e-27kg, V
α=0.052C=15600000m/s
In summary,
Ideal situation, supposes all particles all towards a direction, then the thrust that dipped beam speed particle produces is:
F(t)＝-V
α*M
α*N
mol*M
0*ln(0.5))*(0.5)^(t/T)/(T*M
mol)
Consider actual motion situation, particle is towards all directions homogeneous radiation, and the particle rearward moved produces thrust, then superficial layer is 1/4*F (t) to back pressure integration, and the particle forwards moved is absorbed produces heat, can do other application.Consider the kinetic energy rejection of particle interphase interaction between atomic layer, add correction term η (η <1), the material of its value and atomic layer and shape thicknesses etc. are relevant.The thrust that historical facts or anecdotes border produces is about:
F(t)’＝-V
α*M
α*N
mol*M
0*ln(0.5))*(0.5)^(t/T)*(η/4)/(T*M
mol)
Particularly, as fuel mass M
0=5kg, load-carrying M
1=5kg (only for referencial use, to put aside the load-carrying of practical flight device), M
mol=238kg/mol, initial velocity V
0=16000m/s, supposes correction term η=0.5.
The propelling effect analysis of different half-life decaying particle:
Half life period T=3600s, maximum thrust F '=31.4N;
T=1, maximum thrust F '=3.56e-3N (milli newton level);
T=88, maximum thrust F '=4.08e-5N;
Known, the half life period of nuclear decay material is shorter, and maximum thrust is larger, and accelerator is faster, can need the nuclear matter considering selection corresponding half life period and other performances according to concrete engineering.
Acceleration/accel is different, but the speed that finally can reach under this derivation parameter is all about 3.47e4m/s, far beyond the maximum speed 16Km/s of current human aircraft.
Owing to utilizing the propulsion coefficient of the momentum effect of nuclear decay very high, therefore can reduce to correspondence the counterweight of other propelling units of space craft, thus higher final velocity can be realized.
Propelling unit
At present, the calorific effect that nuclear material decays is used for nuclear energy power generation by the mankind, is heat, drives power generating system to produce electric energy by energy emission and high energy particle kinetic energy by suitable medium reverts.But the momentum effect of nuclear material has not yet to see and is applied to aeronautical field.
Some particles of nuclear material decay release possess very high initial velocity (being greater than 0.001 times of light velocity), and the particle wherein possessing certain mass has larger momentum, its be released leave aircraft while can produce larger reaction thrust to aircraft.Described reaction thrust is applied to propulsion system, a series of tasks of current aeronautical field can be realized with little quality, as produced thrust for a long time in space, continuing to accelerate, thus greatly shortening the time etc. of interplanetary and interstellar navigation.
The utility model provides a kind of for advancing the propelling unit of space craft, described propelling unit is fixed in the agent structure of described space craft, and comprise one or more dipped beam speed particle advancing unit, described dipped beam speed particle advancing unit comprises: push structure, Conversion of Energy structure and adjustment structure, wherein
Described push structure produces dipped beam speed particle, and the dipped beam speed particle that described push structure produces comprises to deviating from (going namely) dipped beam speed particle P ' of described Conversion of Energy structure direction and (namely moving ahead) dipped beam speed particle P to described Conversion of Energy structure side, and the momentum of part described dipped beam speed particle P ' is used directly as the power producing the described space craft flight of propelling;
Described Conversion of Energy structure is fixed on described space craft, for absorbing the dipped beam speed particle P that described push structure produces;
Described adjustment structure is for the dipped beam speed particle P ' that absorbs described push structure and produce thus regulate the momentum of described dipped beam speed particle P '.
In another preference, described adjustment structure is for changing the direction of propulsion of described push structure, the heading of the described dipped beam speed particle P ' that described push structure is produced is consistent with the direction of described aircraft or basically identical, thus adjusts the thrust that the fast particle P ' of described dipped beam produces.
In another preference, described adjustment structure is for regulating the momentum of described particle P '.
Typically, described space craft comprises (but being not limited to): satellite, spacecraft, interplanetary spacecraft.
In another preference, described space craft comprises aircraft body structure and described propelling unit.
In another preference, described space craft also comprises electric system and master control system.
In another preference, described space craft also comprises docking unit, for docked flight device agent structure and described propelling unit.
In the utility model, the position of described dipped beam speed particle advancing unit is not particularly limited, and can adjust according to actual needs.
Usually, described dipped beam speed particle advancing unit is positioned at the outside face of described space craft agent structure and symmetrical.
Typically, described dipped beam speed particle advancing unit is positioned at the rear portion of described space craft agent structure, afterbody, middle part or its combination
In another preference, described multiple dipped beam speed particle advancing unit is connected to form thrust sail structure.
In another preference, described thrust sail structure is preferably fenestral fabric.
In the utility model, produce superposition parallel effect by described thrust sail structure, the reaction thrust effect of described particle P ' to aircraft can be strengthened.
In the utility model, described push structure is positioned at the outside face (namely towards vacuum side) of described Conversion of Energy structure, and described push structure is nuclear decay material coating.
In the utility model, the thickness of described nuclear decay material coating should not be too thick, otherwise the dipped beam speed particle of its decay release can be blocked on coat inside, and the number of particles for generation of reaction thrust is reduced.Correspondingly, this part particle being blocked on coat inside can be exchanged into interior energy owing to clashing into.
Usually, the thickness of described nuclear decay material coating is 1-100 μm, is preferably 3-50 μm, is more preferably 5-30 μm, is 5-15 μm best.
In another preference, described nuclear decay material coating forms primarily of nuclear decay material, with the total weight of described nuclear decay material coating, the content of described nuclear decay material is 10-99wt%, being preferably 30-99wt%, is more preferably 50-99wt%, is 60-90wt% best.
In another preference, the isotopic half life period forming the radio active element of described nuclear decay material is 0.1 second-100 years, is preferably 10 seconds-80 years, more preferably 30 seconds-10 years, 50 seconds-1 year best.
In the utility model, the radio active element forming described nuclear decay material is not particularly limited, and can select according to actual needs.
Typically, plutonium-239 half life period is 2.41 ten thousand, and the half life period of plutonium-238 is 88 years.
In another preference, the nuclear decay of described nuclear decay material is nature nuclear decay.
In another preference, the nuclear decay of described nuclear decay material is non-natural nuclear decay, is preferably the nuclear decay that induced with laser accelerates the half life period.
In the utility model, described nuclear decay material coating can discharge dipped beam speed particle.
Usually, described dipped beam speed particle is any massive particle that can meet or exceed 0.001 times of light velocity (being greater than 300 kilometer per seconds), and these particles can be produced by the decay of multiple nuclear material.For plutonium element, the decay of plutonium element can produce ɑ particle, and its speed is about 0.052 times of light velocity.
In another preference, speed>=3 х 10 of described dipped beam speed particle
4meter per second, preferably>=3 х 10
5meter per second, more preferably>=3 х 10
6meter per second, best>=3 х 10
7meter per second.
In another preference, the speed of described dipped beam speed particle is greater than the millesimal times light velocity.
In another preference, the speed of described dipped beam speed particle is no more than the light velocity.
In another preference, described dipped beam speed particle is massive particle, comprises (but being not limited to): ɑ particle, neutron, proton, electronics or its combination.
In another preference, when needs accelerate described aircraft, the propulsive force Δ F > 0 along described aircraft working direction that described particle P ' produces.
In another preference, when needs slow down described aircraft, the propulsive force Δ F < 0 along described aircraft working direction that described particle P ' produces.
In another preference, when not needing the speed adjusting described aircraft, the propulsive force Δ F=0 along described aircraft working direction that described particle P ' produces.
In another preference, described Δ F is that described particle P ' is to the summation of the propulsive force that described space craft produces.
In the utility model, described Conversion of Energy structure is that decay thermoelectric conversion-counter the pushing away being fixedly connected with described aircraft body structure or being flexibly connected bears structure.
In the utility model, when needing the propulsive force reducing described dipped beam speed particle P ', the momentum of described adjustment structure absorption portion or whole described particle P ', thus reduce or eliminate the thrust for advancing described space craft to fly.
In another preference, described adjustment structure is positioned in described space craft agent structure.
In another preference, the direction of described adjustment structure and/or position can adjust as required.
In another preference, described adjustment structure comprises the material of particle P ' described in Absorbable rod, and its concrete material is not particularly limited, and can adjust according to actual needs.
In another preference, described adjustment structure is aluminium foil.
In another preference, the transformation of energy of absorbed dipped beam speed particle P ' is the form of energy comprising (but being not limited to) by described adjustment structure: luminous energy, mechanical energy, interior (heat) energy, electric energy, nuclear energy electromagnetic energy or its combination.
In the utility model, described propelling unit is also provided with one or more electromagnetic confinement device, and described electromagnetic confinement device is for retraining the heading of described dipped beam speed particle P '.
In the utility model, the charged high-velocity particles of certain angle can be gathered in the direction producing thrust by described electromagnetic confinement device, reaches the strengthening effect to propelling unit.Here, the required electric energy that generates an electromagnetic field can be supplied by the nuclear material of propelling unit self, also can from other energy generating apparatus carry-on, as the electric energy etc. that solar sail is collected.
In another preference, each dipped beam speed particle advancing unit is provided with the electromagnetic confinement device described in; Or multiple dipped beam speed particle advancing unit is provided with a shared described electromagnetic confinement device; Or all dipped beams speed particle advancing unit is provided with a shared described electromagnetic confinement device.
In another preference, described electromagnetic confinement device be positioned at described push structure outside and near described push structure, and the range of movement of the magnetic field that described electromagnetic confinement device the produces particle P ' to radiation outside aircraft push structure that substantially covers that described push structure produces.
In another preference, the electric energy needed for described electromagnetic confinement device is provided by the energy source comprising (but being not limited to): the energy of dipped beam speed particle P that described Conversion of Energy structure absorbs, the non-degenerate electric power of aircraft.
Typically, the non-degenerate electric power of described aircraft comprises (but being not limited to): the electric energy that solar sail is collected, nuclear power power, chemical fuel, all kinds of battery structures such as lithium cell, solar cell, fuel cell, nuclear battery or its combination.
Propulsion method
The utility model additionally provides a kind of method advancing space craft to fly, and described method comprises the steps:
A () provides a space craft, described space craft comprises aircraft body structure and a propelling unit, and wherein said propelling unit comprises described propelling unit;
B () is during space flight, dipped beam speed particle advancing unit in propelling unit described in startup, the momentum of the part or all of described dipped beam speed particle P ' described push structure produced directly is used as to produce the power advancing the flight of described space craft, thus advances space craft flight.
In another preference, described method also comprises: utilize described Conversion of Energy structure to be the energy that can be utilized further by described space craft by the Conversion of Energy of described particle P.
In another preference, described method also comprises: adjustment in use structure absorbs described particle P ', thus the size of the propulsive force regulating described particle P ' to produce and/or direction.
In another preference, described method also comprises: use electromagnetic confinement device to retrain described particle P ', thus regulates size and/or the direction of propulsive force, thus described space craft is carried out to the adjustment of flying speed and/or flight orientation.
In another preference, described method is used for space environment.
Propulsion method described in the utility model to propelling time of space craft mainly based on the decay period of adopted nuclear fuel material.Because the decay period of most of nuclear fuel material is all longer, therefore, scheme described in the utility model is larger in spatial extent, and under the condition that the time is longer, its advantage is more remarkable.
Compared with prior art, the utility model has following major advantage:
(1) nuclear fuel material that can be limited provides long-term propulsive force to aircraft;
(2) can adjust the attitude of aircraft while propulsion aircraft;
(3) high fltting speed can be provided to aircraft;
Below in conjunction with specific embodiment, set forth the utility model further.Should be understood that these embodiments are only not used in restriction scope of the present utility model for illustration of the utility model.The experimental technique of unreceipted actual conditions in the following example, the usually conveniently conditioned disjunction condition of advising according to manufacturer.Unless otherwise indicated, otherwise percentum and number calculate by weight.
Unless otherwise defined, all specialties used in literary composition and scientific words and one skilled in the art the meaning be familiar with identical.In addition, any method similar or impartial to described content and material all can be applicable in the utility model method.The use that better implementation method described in literary composition and material only present a demonstration.
Embodiment 1
Fig. 1 is the effect schematic diagram of the utility model propelling unit and space craft.Wherein, can produce the material of nuclear decay, if the half life period is the plutonium-238 of 88 years, be applied to the body structure surface of propelling unit towards vacuum, the opposite side of overlay is thermoelectricity transformational structure.Leave overlay certain distance and have adjustment structure, to the ɑ particle that decay produces, adjustment structure can use aluminium foil class lightweight construction.In vacuum, the ɑ particle of nuclear decay material coating sustained release 0.052 times of light velocity, the high energy particle towards thermoelectric conversion structure is converted into heat energy, and then is converted into electric energy, for the electric power supply of aircraft; ɑ particle momentum effect towards vacuum superposes, and forms thrust.Adjustment structure is attached in aircraft body structure, and when being in coating radiation path, meeting absorbing particle kinetic energy, adjusts the material shielded area of this part, position, just can regulate the size and Orientation of thrust.Above-mentioned thermoelectric structure, push structure form dipped beam speed particle advancing unit together with adjustment structure, the dipped beam speed particle advancing system of multiple (N number of) propulsion unit composition aircraft.The master control system of aircraft controls dipped beam speed particle advancing system and other position, its auxiliary power system, as solar sail or other electric power supply system, suitable electromagnetic field can be set up together with nuclear decay thermoelectricity, for more charged particle kinetic energy being adjusted to the direction being beneficial to and producing thrust.
Embodiment 2
Fig. 3 is the momentum balance figure of the utility model dipped beam speed particle advancing unit.As can be seen from Figure 3, although High energy particles Radiation is close to space uniform radiation, because the kinetic transformation towards aircraft is heat energy, momentum is unbalance, and the overall storage effect of the particle momentum towards vacuum is for producing deboost.Solid arrow is particle radiation direction, upper and lower application force homeostasis in figure, but horizontal direction then creates thrust due to asymmetric.
Embodiment 3
Fig. 4 is the momentum balance figure that the utility model arranges the dipped beam speed particle advancing unit of electromagnetic confinement device.After introducing electromagnetic confinement device, described electromagnetic confinement device can adjust charged particle travel direction, makes more momentum for generation of the thrust in required direction.
The electric power setting up electromagnetic field can come from the non-degenerate electric power of aircraft, as solar sail or nuclear power power etc.
Embodiment 4
Fig. 5 is the thrust sail schematic diagram that the utility model dipped beam speed particle advancing unit is formed.Wherein, dipped beam speed particle advancing unit can be connected to become thrust sail one by one, just as solar sail, aloft launches in due course, makes full use of large area and produce large overall thrust.
Embodiment 5
Fig. 6 is the general illustration of the space craft arranging the utility model propelling unit.Wherein, described aircraft can adopt conventional motive system to launch, make aircraft reach escape gravitation raw velocity and after entering space, this thrust sail thrust sail launched, although can be realized continuing to produce limited lasting thrust and thermopower in very long route by very limited nuclear fuel material again.
The all documents mentioned at the utility model are quoted as a reference all in this application, are just quoted separately as a reference as each section of document.In addition should be understood that those skilled in the art can make various changes or modifications the utility model, and these equivalent form of values fall within the application's appended claims limited range equally after having read above-mentioned instruction content of the present utility model.
Claims (7)
1. a dipped beam speed particle advancing system, it is characterized in that, described propulsion system is fixed in the agent structure of a space craft, and comprise one or more dipped beam speed particle advancing unit, described dipped beam speed particle advancing unit comprises: push structure, Conversion of Energy structure and adjustment structure, wherein
Described push structure produces dipped beam speed particle, and the dipped beam speed particle that described push structure produces comprises to deviating from the dipped beam speed particle P ' of described Conversion of Energy structure direction and the dipped beam speed particle P to described Conversion of Energy structure side, and the momentum of part described dipped beam speed particle P ' is used directly as the power producing and advance the flight of described space craft;
Described Conversion of Energy structure is fixed on described space craft, for absorbing the dipped beam speed particle P that described push structure produces;
Described adjustment structure is for the dipped beam speed particle P ' that absorbs described push structure and produce thus regulate the momentum of described dipped beam speed particle P '.
2. the system as claimed in claim 1, is characterized in that, described dipped beam speed particle advancing unit is positioned at the outside face of described space craft agent structure and symmetrical.
3. the system as claimed in claim 1, is characterized in that, described push structure is positioned at the outside face of described Conversion of Energy structure, and described push structure is nuclear decay material coating.
4. system as claimed in claim 3, is characterized in that, described nuclear decay material coating can discharge dipped beam speed particle.
5. the system as claimed in claim 1, is characterized in that, described Conversion of Energy structure is that decay thermoelectric conversion-counter the pushing away being fixedly connected with described aircraft body structure or being flexibly connected bears structure.
6. the system as claimed in claim 1, is characterized in that, described propulsion system is also provided with one or more electromagnetic confinement device, and described electromagnetic confinement device is for retraining the heading of described dipped beam speed particle P '.
7. a space craft, is characterized in that, described space craft comprises propulsion system according to claim 1.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520280345.7U CN204737044U (en) | 2015-04-30 | 2015-04-30 | Fast particle propulsion system of short -distance beam reaches space flight ware including this system |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104773307A (en) * | 2015-04-30 | 2015-07-15 | 中国科学院宁波材料技术与工程研究所 | Approximate-light-speed particle moving method and system |
| CN106809397A (en) * | 2015-11-30 | 2017-06-09 | 黄鹏搏 | A kind of accelerator does the ROV of drive device |
-
2015
- 2015-04-30 CN CN201520280345.7U patent/CN204737044U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104773307A (en) * | 2015-04-30 | 2015-07-15 | 中国科学院宁波材料技术与工程研究所 | Approximate-light-speed particle moving method and system |
| CN106809397A (en) * | 2015-11-30 | 2017-06-09 | 黄鹏搏 | A kind of accelerator does the ROV of drive device |
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