DE10252895A1 - Obtaining ballast for lighter-than-air aircraft, involves separating particles from ambient atmosphere around vehicle by generating electric field as thin film on outer or inner surface of vehicle - Google Patents

Abstract

The method involves separating particles from the ambient atmosphere around the aircraft (L) by generating an electric field as a thin film on an outer or inner surface of the aircraft provide for this purpose. The electric charge on the exterior of the aircraft caused by the movement of the aircraft is used to separate particles from the surrounding air. AN Independent claim is also included for the following: (a) an arrangement for obtaining ballast for lighter-than-air aircraft, especially for implementing the inventive method.

Description

The invention relates to a method and an arrangement for obtaining ballast for aircraft lighter than Air.

When operating an airship with a filling from carrier gas results from the during fuel used during the journey is a continuous decrease in the weight to be balanced or carried by the lifting gas. For airships With hydrogen as the carrier gas, weight loss has become the state of the art by releasing the lifting gas and thus reducing the lifting capacity accordingly balanced. In modern airships with helium filling this method is no longer possible for economic reasons. On Airship must board during the ride mass is gained / regained in the form of ballast.

From the publication DE-PS 465 461 a method and a device for obtaining ballast from the exhaust gases of the engines of the airships are known. The gases are led to their cooling through hollow blades of the propellers used to operate the airship. The water precipitating in the propeller is collected by appropriately trained devices arranged around the propeller.

The US airships "Akron" and "Macon" were with air-cooled ballast water extraction systems fitted. The heat exchangers used enlarged the Air resistance significantly and required a very complex cleaning and maintenance.

In the VDI magazine vol. 83, no. 15, (1939) describes the ballast water extraction in the airship LZ 130. The exhaust gases from the piston engines used there flow through a three-stage cooler. In the first stage, the hot exhaust gas is created using ambient air flowing around it of 500 ° C to approx. 400 ° C cooled. In a water cooler In the second stage, an exhaust gas temperature of 50 ° C is reached. In a final air-cooled heat exchangers the exhaust gas is about 5 ° C above ambient temperature cooled. With piston engines it was possible with such a system under certain conditions a weight compensation of the fuel consumption can be achieved. These plants were big and heavy and caused a considerable amount depending on the cooler design additional Air resistance or a loss in efficiency of the drives of the Airship.

The transfer of this technique to modern diesel engines or shaft power gas turbines is only with great Additional effort possible and leads to unacceptable technical solutions. Gas turbines are operated with a much higher excess air. In order to the "dew point" of the exhaust gases also drops. The means a higher one cooling requirements for a larger mass throughput.

Generally known in the art is to use electrostatic precipitators as an electrical gas cleaning system. With systems for electrostatic dedusting of exhaust gases with the help of direct current pass through at high voltage with dust Exhausts an electric field. The dust particles are charged and finally on metal wires or sheets deposited.

From the publication DE-AS 1 466 075 an arrangement for avoiding static charges in aircraft is also known. This arrangement is used for low-flying aircraft, from which a spray of a treatment agent which is electrically charged against earth potential is released onto the underlying vegetation. The electrical charging of the treatment substance requires a high electrostatic field between the delivery point of the treatment material and the plants to be treated which are at earth potential, so that a large uniformity of the distribution of the treatment substance is brought about. This is achieved in that there is an adjustable high-voltage generator between the discharge electrode and the aircraft body, the voltage of which is regulated in such a way that the electric field strength corresponds to the atmosphere directly surrounding the aircraft.

Therefore, the invention is the Underlying problem, an improved method and arrangement to obtain ballast for Aircraft easier than proposing air.

According to the invention, the problem is solved by the characteristics of the claims 1, 8 and 9. Further developments of the invention are described in the dependent claims.

This problem is solved according to the invention solved, that the process of obtaining ballast for aircraft is easier than Air through separation of particles from the air or ambient atmosphere on body surfaces accomplished is that the particles are used to gain ballast and / or cleaning air by creating an electrical field as a thin layer on the surface or in lighter than air (LTA) aircraft, especially airships, be deposited.

In addition, the electrical Charging the case by moving the LTA aircraft to separate particles be exploited.

The procedure is followed by a few more Methods with a synergistic effect further developed according to claims 3 to 8th.

Different arrangements, especially for Realization of the procedure are possible. In a first arrangement according to the invention is the shell of an LTA aircraft approximately in the middle in the longitudinal direction by an electrical one Insulation divided into an upper and a lower half of the shell, which with a regulated high voltage generator.

In one embodiment of the invention Shell material arranged a plurality of thin mats made of conductive material and connected in the respective shell half with each other and a pole of the high voltage generator, the capacitive mats arranged in a distributed matrix. It is expedient that the mats are integrated into the layer structure of the casing material.

It's different for getting Functions of an airship necessary that important functional parts of the LTA aircraft is not included in the electrostatic field but kept free.

In an embodiment of the invention to generate the required electrostatic forces Coating suitable coatings applied to the shell material. It it is appropriate that on LTA aircraft rainwater collection devices are arranged their purpose later discussed becomes.

In a further embodiment, the High-voltage generator from the existing electrical system fed. The high voltage generator is designed to reverse the electrical Allow cargo.

In an embodiment of the invention at various points on the LTA aircraft probe for the existing field strength arranged.

In a second arrangement according to the invention leads in longitudinal direction an axial air duct through the LTA aircraft around which the rear area extends a coaxial capacitor. At the top Plate is connected to a high voltage generator and under it lower plate a collecting area with collecting container arranged.

It may be appropriate for the movement the air flow in the air duct is accelerated by a fan.

According to the invention, one takes place at periodic time intervals Charge reversal on the coaxial capacitor and thus a drop in Macro particles in the collecting area, being at periodic intervals a promotion the deposited macroparticles of the collecting area into a collecting container can.

After a third supplementary Arrangement are used to generate an ionized gas flow within the shell of the LTA aircraft approximately in the middle of its ionization chambers Form of high-voltage discharge devices arranged, which a circulation device for generating circulation flows the gas along the inner wall of the shell is arranged.

Circulated in an embodiment of the invention the ionized gas within the envelope of the LTA aircraft a system of electrically powered fans and / or convection currents. A Heating the carrier gas to increase the buoyancy generates the convection currents additional Use.

In a further embodiment, the shell material an accumulation and distribution of the ionized by circulation of Gases generated electrical charge on the inside of the case on the outside enable. According to the invention Charge distribution on the surface of the shell change the direction and speed of circulation of the ionized Gases and its volume adjustable.

It is necessary that the high voltage discharge devices shielded from the electro-magnetic fields by a Faraday cage and important functional parts of the LTA aircraft are not in the electrostatic field are included. Again, it is advisable that on LTA aircraft in addition Fall arrest devices for Rainwater are arranged. In all arrangements, the expert can according to the teaching of the invention a compensation of the shift in the center of gravity by the mass of the separated macroparticles by means of internal Trim device of the LTA aircraft balance.

The invention will follow embodiments explained in more detail under Inclusion of a drawing with basic representations of possible embodiments the invention:

Show it:

1 : a first embodiment of the invention;

2 : a second embodiment of the invention;

3 : a third embodiment of the invention.

• – eine Luftschiff-Hülle hat eine Oberfläche von etwa 42.000 m²;
• – ein großes Lasten-Luftschiff verbraucht für eine Langstreckenmission etwa 40 t Treibstoff.

The basic assumption for the invention is based on the following:

• - An airship hull has a surface area of approximately 42,000 m ² ;
• - A large cargo airship consumes around 40 tons of fuel for a long-range mission.

The loss of mass due to fuel consumption must be compensated for by a ballast intake. By inducing an electrostatic charge on the shell surface, it is possible to obtain a layer of particles that are extracted from the contaminants in the outside air. Assuming an average macro particle density of 1000 kg / m ³ , a layer of 1 mm must be built up on the surface in order to achieve the necessary ballast.

The deposition method according to the invention of particles from the air on body surfaces executed so that the separation of particles to obtain ballast and / or Purification of the air by creating an electric field as a thin one Layer on the surface or within lighter than air (LTA) aircraft, in particular Airships.

In addition, the electrical Charging the case by moving the LTA aircraft to separate particles be exploited.

• – Nutzung des Luftschiff-Stromerzeugungssystems zum Aufbau einer Ladung über eine Matrix aus kapazitiven Matten auf oder in der Hülle. (1)
• – Nutzung der elektrostatischen Kräfte durch Reibungseffekte infolge der Bewegung des Luftschiffes durch die Luft mit geeigneten Beschichtungen oder Hüllenmaterialien. (in Kombination mit anderen Lösungen)
• – Abscheidung von Makroteilchen, die durch einen axialen Kanal in das Innere des Luftschiffes gelangen. (2)
• – Zirkulation eines ionisierten Gases innerhalb der Heliumfüllung zur Unterstützung des elektrostatischen Effektes an der Hüllenoberfläche. (3)

To implement the invention Several principle arrangements and their combination are possible in order to achieve an improved and more flexible solution. These are arrangements based on the following principles:

• - Use of the airship power generation system to build a charge over a matrix of capacitive mats on or in the shell. ( 1 )
• - Use of the electrostatic forces due to friction effects due to the movement of the airship through the air with suitable coatings or shell materials. (in combination with other solutions)
• - Separation of macro particles that get into the interior of the airship through an axial channel. ( 2 )
• - Circulation of an ionized gas within the helium filling to support the electrostatic effect on the shell surface. ( 3 )

On board an airship L there is an electrical power system that supplies both a three-phase and a direct voltage network. To generate the after 1 required electrostatic fields, a voltage of about 10 kV is required to ensure the initial adhesion of the first macro particle layer. Despite the high voltage, the power required to generate the field is very low compared to the total electrical energy requirement. The high voltage is also not constantly required.

To generate the high voltage in general known arrangements, e.g. a voltage multiplier electronics, be used.

To 1 the envelope of the airship L is divided lengthways by electrical insulation 1 into an upper O and a lower half U of the envelope. To the conductive mesh grid embedded in a matrix arrangement on the surface of the airship hull or most appropriately in the hull fabric structure O; U a pole of the high voltage generator is applied. The charge is thus distributed largely in the same way as in a flat capacitor. The thickness of the macroparticle layer is controlled by regulating the level of the voltage and the residence time of the generated electrostatic field. Since the induced electrostatic charges in the shell cause a further attraction of macro particles by the movement of the airship L after the first layers have been built up, the high voltage can be switched off. A charge reversal by switching the poles of the high voltage generator G is necessary in order to control the structure of the macroparticle layer and to be able to drop it at the end of the mission of the airship L.

The long-range missions of Lightning protection system required by airships is proposed by the Arrangement not negatively affected. Taken under cloud conditions a static charge due to the movement of the airship and the shell structure, but which is included by the invention in the regulation of the field strength.

Extreme weather conditions, such as Heavy rain and storm require measures that result in mass loss by partial detachment balance the accumulated layer of macro particles. So it is appropriate to the airship hull Provide devices for absorbing rainwater.

In the 2 an arrangement for separating the macro particles inside the airship L is shown. The airflow containing the macroparticles enters an axial air duct LK, which runs from the bow to the stern of the airship L. The speed of the air flow can be increased by fans in the air duct LK. A charging device arranged around the air duct LK in the form of a coaxial capacitor K, which extends over a distance resulting from the required area along the air duct LK, serves to attract the macro particles by means of an electrostatic charge induced by a high-voltage generator G. By applying a reverse charge to this coaxial capacitor K, the macroparticles are released at regular intervals from the charged surfaces into a collecting area A underneath. This collecting area A can be designed in the manner of an inclined plane. From this collecting area A, the accumulated mass of macro particles is periodically discharged into a collecting container, for example by a conveyor belt. The advantage of this arrangement is that the accumulated macroparticles actually exist within the airship L. This avoids the problem of possible loss due to heavy rain or wind.

The in the 3 The arrangement shown is used to generate and circulate ionized gases in the airship. The use of high-voltage discharge devices as ionization chambers IK, which are arranged approximately in the middle of the airship L, facilitates the generation of an ionized gas stream. A circulation device Z is arranged in front of the ionization chamber IK, through which and a system of further fans and / or convection currents the ionized gas circulates within the shell. The convection currents arise during the heat exchange with the helium filling. The ionized gas is circulated to ensure that a charge is applied to the inner surface of the shell. Certain requirements are placed on the material properties of the casing. The material must easily accumulate and distribute static charges so that the formation of a macro particle layer on the outer surface of the shell is made possible. The direction and speed of the circulation of the ionized gas together with its volume determine the charge distribution on the shell.

To the high-voltage discharge devices have to go around special arrangements in the form of a Faraday cage were made to the airship systems against the effects of electromagnetic Shield fields.

When choosing the one to be ionized Gases had a number of important properties to take into account the crucial for one good charge distribution.

To the impact on the load capacity of helium, the density must be low. Since that Ionized gas tries to get back with the detached electrons to connect, the recombination tendency must be low. Around the energy requirement for operating the unloading device low hold, the gas must require a low ionization energy.

The circulation of the ionized gas is said to create a moving layer that is in contact with the inner surface of the envelope. additionally The ions of the denser one act to electrostatically charge the shell Gases as a separating layer that limits the migration of the helium atoms. The has a positive impact on operating costs.

Various circumstances must also be taken into account in the practical interpretation of the proposed arrangements:
To control / regulate the system operation, a detection of the voltage differences and / or a charge measurement are required.

The air flow over certain areas of the Shell can prevent the formation of a layer of macro particles. It can from high surface speeds surrender to local forces the stronger are than the electrostatic forces.

The structure of the particle layer in certain areas of the envelope can have negative effects on airship operations, such as e.g. the flight control surfaces.

A deposit in such areas is prevented by appropriate construction. When creating one Airship on the mast is assumed to be prior to manufacture Connection to the mast the unloading is already completed. The the same applies to the handling of the airship. Then the shell to the macro particle layer to be able to build to accommodate a higher one Load handling, these handling procedures must be adapted accordingly.

When flying through heavy rain the risk that the adhering particles are partially or completely "washed off". The mass accumulation is therefore supplemented by a rainwater detection system.

The invention can be characterized by a further Adaptation of the static shell charge can also be used to reduce the risk of lightning strikes. By reducing the potential difference between the airship and the surrounding area can reduce the likelihood of lightning strikes become. The necessary ones But tensions are greater than the values required to gain mass.

The invention is particularly for ballast extraction easier as a mass balance for fuel consumption in aircraft suitable as air. The energy consumption is low. There will be none substances harmful to the environment are used and none are produced such substances.

Since an airship with the solution according to the invention also This can also collect dirt and pollutants from the air for air purification over areas with particles that pollute the environment become.

I

electrical insulation

G

High voltage generator

O

upper half shell

U

lower half shell

L

airship

LK

axial air duct

K

Coaxial condenser

A

collecting area

IK

Oonisationskammer

Z

circulation means

Claims (26)

Method for obtaining ballast for aircraft lighter than air, characterized in that particles from the ambient atmosphere of the vehicle are deposited as a thin layer on the outside or inside of the vehicle on a surface of the vehicle prepared for this purpose by generating an electric field. A method according to claim 1, characterized in that the electrical charge of the case is caused by the movement of the LTA aircraft is used to separate particles. A method according to claim 1 or 2, characterized in that that within the vehicle in a lengthwise direction extending axial air duct (LK) in the rear area a coaxial capacitor (K) is used as the deposition surface, on the a plate of the high voltage generator (G) for generating a electrical field is connected and among others, preferably lower, plate on a collecting surface (A) with collecting container separated particles are collected. Method according to one of the preceding claims, characterized in that the electrical charge is reversed at periodic time intervals is reversed on the coaxial capacitor (K) and thus a fall of the macro particles into the collecting surface (A) is controlled. Method according to one of the preceding claims, characterized characterized that in the envelope for the Traggas an ionized gas is generated and circulated in such a way that it ensures the application of a charge on the inner surface of the shell. Method according to one of the preceding claims, characterized characterized that the lifting gas to increase buoyancy and Convection power generation of ionized gas is heated. Method according to one of the preceding claims, characterized characterized that a possible shift in the center of gravity of the Vehicle by the mass of the separated particles by means of a internal trim of the LTA aircraft. Application of the method according to one of the preceding Expectations, for temporary Cleaning the atmosphere in certain regions above the Earth. Arrangement for obtaining ballast for aircraft lighter than air, especially to carry out the method according to a of the preceding claims, characterized in that the outer skin surface of the or a surface in the LTA aircraft communicates with a regulated high voltage generator (G). Arrangement according to claim 9, characterized in that the outer shell about in the middle in the longitudinal direction by electrical insulation (I) into an upper (O) and a lower shell half (U) is divided. Arrangement according to one of the preceding claims, characterized marked that on the shell material a variety of thinner Mats made of conductive Material arranged and in the respective shell half (O; U) with each other and a pole of the high voltage generator (G) are connected. Arrangement according to one of the preceding claims, characterized characterized that the capacitive mats in a distributed Matrix are arranged. Arrangement according to one of the preceding claims, characterized characterized in that the mats in the layer structure of the shell material are involved. Arrangement according to one of the preceding claims, characterized characterized that to generate the necessary electrostatic Powers through Coating suitable coatings are applied to the shell material. Arrangement according to one of the preceding claims, characterized characterized in that the high voltage generator (G) from the existing electrical system power generation system is fed. Arrangement according to one of the preceding claims, characterized characterized in that the high voltage generator (G) reverses charge allows. Arrangement according to one of the preceding claims, characterized labeled that at various points on the LTA aircraft probe for the existing field strength are arranged. Arrangement according to one of the preceding claims, characterized characterized in that the surface lying inside the vehicle as longitudinal extending axial air duct (LK) through the LTA aircraft is formed around which there is a coaxial capacitor in the rear region (K) extends on the upper plate of the high voltage generator (G) is connected and under the lower plate there is a collecting area (A) with collecting container is arranged. Arrangement according to claim 18, characterized in that the movement of the air flow in the air duct (LK) is accelerated by a fan. Arrangement according to one of the preceding claims, characterized characterized that to generate an ionized gas stream inside the envelope of the LTA aircraft approximately in its center ionization chambers (IK) in the form of high voltage discharge devices are arranged, which a circulation device (Z) for generation of circulation currents the gas along the inner wall of the shell is arranged. Arrangement according to one of the preceding claims, characterized characterized that the circulation device as a system electrically powered blower and / or convection power generators for the ionized gas is. Arrangement according to one of the preceding claims, characterized through a material for the case of the aircraft that is suitable, accumulation and distribution the electrical generated by circulation of the ionized gas Charge on the inside of the case to the outside to effect. Arrangement according to one of the preceding Claims, characterized in that the charge distribution on the outer surface of the shell can be adjusted by changing the direction and speed of the circulation of the ionized gas and its volume. Arrangement according to one of the preceding claims, characterized characterized in that the high-voltage discharge devices against the electromagnetic fields are shielded by a Faraday cage are. Arrangement according to one of the preceding claims, characterized marked that important functional parts of the LTA aircraft are not included in the electrostatic field. Arrangement according to one of the preceding claims, characterized marked that on the LTA aircraft rainwater collection facilities are arranged.