RU2506204C1 - Method of locating high-altitude platform and high-altitude platform - Google Patents

Abstract

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering. Proposed platform comprises bundle of aircraft coupled by flexible rope transmitting forces and incorporating electric power transmission and control signal channels. One of said aircraft carries windmill. Method of locating high-altitude platform consists in locating aircraft in stable wind flows displacing at different speed relative to earth and/or different directions. Besides, it includes retaining said bundle at preset point or its displacement relative to earth in preset direction by aerodynamic controls and power plants. Difference in energy of wind flows is used at invariable flight altitude to said end as well as power generated by windmill at one aircraft and transmitted to other aircraft. Payload is arranged at aircraft or connection rope.

EFFECT: longer high-altitude flight.

4 cl, 5 dwg

Description

The invention relates to the field of aviation and aeronautics and can be used to create a high-altitude stratospheric platform, which is an alternative to geostationary spacecraft. The high-altitude platform is designed to lift the payload to an altitude of 15-25 km (the height of the bicycle and tropopause) and is able to stay at a given point for a long time.

Several options are known for creating a high-altitude stratospheric platform using an aerostatic module (high-altitude airship) and an aircraft module, as well as hybrid options.

The completed project of a high-altitude airship with a solar-powered propulsion system is most fully reflected in US Pat. No. 6,607,163 B2 dated 08.19.2003, IPC B64B 29/00. In accordance with the design described in the patent, a high-rise airship was built and successfully tested.

In the patent US 4415133 from 11/15/1983, IPC B64D 27/02 shows the design of a high-altitude aircraft with a solar power plant. This design is characterized by an original combination of vertical and horizontal surfaces that create lift and serve to accommodate solar cells. Currently, there are several known projects of experimental high-altitude solar-powered aircraft with a long flight duration - Helios, Centurion, NASAPathfinder-Plus (http://www.nasa.gov/centers/dryden /news/FactSheets/FS-054-DFRC.htmn )

These experimental devices are designed to use solar energy during daylight hours and the energy accumulated during the day to hold them at night at a given point in space relative to the earth. The bulk of the energy in the case of the implementation of the aerostatic option is necessary to move the high-altitude airship in the atmosphere with the speed of the wind flow and hold it at a given point relative to the earth's surface.

Aircraft version consumes the energy necessary to create aerodynamic lift, and, as a rule, has a cruising speed exceeding the speed of the wind flow.

The use of solar energy allows for these types of aircraft to achieve theoretically unlimited flight duration. Currently, a flight duration of several days has been achieved for the aircraft version, but for flights in the equatorial zone.

However, these concepts have a number of significant drawbacks. The use of solar energy requires the placement of solar cells on the aircraft structure (in the wing and stabilizer for the aircraft version, on the shell or a special pylon for the airship) and the storage system, which in total make up more than 50% of the take-off weight of the aircraft and are the main factor affecting the size and the cost of the aircraft. At the same time, the payload mass is only 3-8% of the total take-off weight when implementing the option designed for continuous year-round barrage. The role of these factors increases when designing a high-altitude platform for flights in latitudes of 50-60 ° north latitude (N), which is especially important for our country.

A known method and device for creating bundles of aircraft for the implementation of high-altitude platform. For example, European patent EP 0385921 B1 from 09/05/1990, IPC B64D 1/22, B64D 27/24, B64C 37/02, taken as a prototype. This patent describes a bunch of aircraft (LA), which is an aerostatic aircraft connected via cable cables to three unmanned aircraft, which, moving along a circular path relative to the attachment point, provide the aerostatic aircraft with fixation at a given point in space. The necessary effort and movement of the system in the direction opposite to the direction of the air flow relative to the earth occurs due to the tension of the cable connecting the unmanned aircraft with the aerostatic apparatus during its movement in the sector of the circle coinciding with the required displacement vector.

The payload is placed on an aerostatic apparatus. Unmanned aircraft have the most simplified design and electric power plant.

There are several options for powering the platform: by means of a solar cell battery placed on a balloon; by transmitting microwave energy from a ground station to an antenna located on a balloon; using a cable from a ground source. Energy is transferred from the aerostat to unmanned aerial vehicles via cable cables connecting them.

Powering the entire platform through solar energy has the drawbacks already described above for ensuring long-term flight. The use of microwave energy will require the creation of a powerful transmitting station. The transmission of electricity through a cable to a height above 15,000 m will require a large cable length, and, accordingly, its mass will be a significant proportion of the mass of the entire system. Also, the last 2 options for energy supply do not provide mobility of the complex. This system does not use wind flow energy.

The objective and technical result of the present invention is the creation of a high-altitude platform that uses the energy of wind flows and provides continuous barrage while maintaining a low cost of the system itself and the cost of its life cycle.

The technical result is achieved by the fact that in the method of placing a high-altitude platform consisting of a bunch of aircraft, which consists in raising the platform to a predetermined height, supplying energy and holding it at a given point, the aircraft are placed in stable wind currents moving at different speeds relative to the ground and ( or) in a different direction, and the retention of a given bundle at a given point or its movement relative to the ground in a given direction is ensured by aerodynamic controls power plants of several aircraft of the bunch, using the energy difference of the wind flows while maintaining a constant flight height, and (or) due to the energy received from the wind generator installed on one of the aircraft of the bunch, and transmitted through a cable cable to power plants of others (other) aircraft, with the payload being placed either on the aircraft or on a cable cable connecting the aircraft.

The technical result is also achieved by the fact that the high-altitude platform, including a bunch of several aircraft equipped with aerodynamic controls, automatic control systems and power plants and interconnected by means of a flexible cable, which provides power transmission and contains transmission channels of electricity and an information control signal from one device to another, contains in conjunction any type of aircraft, moreover, on one of the aircraft with yazki installed wind turbine.

The technical result is also achieved by the fact that the high-altitude platform, including a bunch of several aircraft, includes aircraft of the same types.

The technical result is also achieved by the fact that the high-altitude platform, including a bunch of several aircraft, includes aircraft of various types.

Figure 1 - high-altitude platform - a bunch of aircraft.

Figure 2 - latitudinal distribution of wind speeds and directions in the summer.

Figure 3 is an embodiment of a bundle of a tethered balloon and a parachute system.

Figure 4 is an embodiment of a bundle of a glider with a wind generator and an airplane with an electric power plant.

Figure 5 - diagram of the forces acting on the bunch.

High-altitude platform - a bunch of aircraft, as shown in figure 1, is an aircraft LA1 and LA2, located at different heights H ₁ and H ₂ , interconnected by a cable cable 3, which provides the transmission of loads, electricity and control signal from one aircraft to another. Wind generator 4 is located on LA1, and a power plant with electric motor 5 is located on LA2. Reverse placement of the wind generator and power plant is also possible, or both aircraft can be equipped with a wind generator and power plant depending on the wind conditions of the high-altitude platform’s flight, size and direction of air speed threads V _p1 and V _p2 .

If necessary, LA1 and LA2 can have an electric power storage system 6 (storage batteries, capacitor banks, an accumulation system using an electrochemical generator) to compensate for diurnal fluctuations in the speed of wind flows. The payload 7 can be placed both on the LA1, and on the LA2, as well as on the cable, if you need the placement of the antenna elements to ensure relaying. This diagram in FIG. 1 describes a structural diagram of a bundle of 2 aircraft, however, if necessary, a larger number of aircraft may be included in the bundle.

The essence of this invention is to use the energy of the wind flows of the Earth’s atmosphere, moving at different speeds and (or) in different directions. It is most realistic to use heights of 17-23 km to implement this idea. Studies of the atmosphere at altitudes of 15-25 km showed (Fig. 2) that in this range of heights there are constant flows of air masses from the equator to the poles at altitudes of 15-19 km and in the opposite direction of 19-25 km. The border zone between these opposite streams is called a bicycle pause and is characterized by a low wind speed of 0-15 m / s relative to the ground during the summer period (from April to November).

The dimensions of this zone in height can be ~ 2-3 km. Thus, we have two air media moving in opposite directions relative to the earth’s surface and delimited by a transitional region in summer.

In winter, in the altitude range of 15–25 km, there are boundary altitudinal zones with the same wind direction, but with a significant difference in the speed of the wind flow. These currents are quite stable throughout the calendar year and operate in areas from the equatorial zone to the northern and southern polar circles.

Having positioned the aircraft so that it has a physical connection between two opposing streams or streams having a significant difference in speed, the energy of moving media is used to hold the device at a given point and (or) to move it at a low speed. This method of movement is similar to the principle of movement of a sailing ship using wind energy to move on the surface of the water. In order for the aircraft to have contact with two air currents, it is necessary that it has the appropriate dimensions that overlap the dimensions of the tropopause. Achieving such dimensions with one aircraft is a difficult task solution and economically inexpedient.

Two aircraft are positioned so that they are in air currents having the required difference in speed relative to the ground, above a given point at different heights, and connect them with a cable. In this case, a combination of any types of aircraft in such a bundle is possible.

In the practical implementation of this idea, an optimal choice of aircraft is required, corresponding to the required speed range at given heights and having the best specific weight and cost indices. For the totality of the existing climatic conditions, a combination of two aircraft can be implemented in the following options described below.

The first option is supposed to be the simplest and most logical for the conditions of a summer cycle pause. In the presence of two wind streams at different heights, having the opposite direction relative to a fixed point on the earth's surface, each of the aircraft is located in these streams and connected by a cable cable 3, as shown in Fig. 1. Balance the drag force of each aircraft using the effective lift for all aircraft, the maximum possible at given air flow rates. For these conditions, the following combination of different types of aircraft is used (Fig. 3): the upper (main) aircraft LA1 is a tethered balloon, the total lifting force of which corresponds to the total weight of its own structure, the weight of the cable and payload, and the lower or auxiliary LA2 is a paraglider (parachute-wing), bearing the function of a sail and a control element.

It is possible to use any type of aircraft in this system, for example, a glider or a gyroplane with an autorotating screw. However, it should be noted that these types of aircraft, unlike a tethered balloon, whose aerostatic lift is independent of airspeed, have a range of application limited by the minimum wind speed, i.e. their minimum airspeed should not be less than the stall speed for this particular type of aircraft. The proposed combination option, depicted in figure 3, has the minimum required range of the difference in speed of wind flows and, therefore, an expanded scope for geographical and climatic parameters.

Such a combination of aircraft in conjunction (Fig. 3) practically makes it possible to balance the system not only under conditions of a bicycle pause, but also in the presence of a difference in the speeds of wind flows along heights having one direction relative to the ground. Only in this case can we consider the equilibrium of the system in space moving with a certain speed and having the ability to move in directions perpendicular to air flows. Such a system also has advantages over conventional free balloons, since it allows you to maintain a given flight altitude without additional energy, fuel or ballast and has an unlimited flight duration.

The second option is a sequential complication of the first and is focused on more common atmospheric conditions, when wind flows at different heights have the same (mostly western direction), but have a significant difference in speed:

ΔV = V _p1 -V _p2 ,

where V _p1 - flow rate at a height of H ₁ , V _p2 - flow rate at a height of H ₂ .

For example, for the conditions of Dixon Island in the month of January, the difference in wind speed ΔV over heights of 16 and 24 km is up to 14 m / s.

In this situation, to fix the system relative to a given point on the earth's surface, both aircraft must move against the direction of wind flows. To implement this idea, a cable cable 3 is used for energy exchange between connected aircraft (Fig. 4). As follows from the wind profile, the upper LA1 will be in a stream with a high speed. A wind generator 4 (an analogue of the backup power system for civilian aircraft) is installed on it, which generates electricity and transfers it to the lower LA2 via a cable cable. In this case, the lower LA2 becomes the main one and carries the payload 7, since it moves in the stream at a lower speed, but with a higher air density. Structurally, both aircraft correspond to an aircraft with a large elongation wing and area for flights at high altitudes. The lifting force of the upper LA1 must balance the weight of the cable cable 3, wind generator 4 and the weight of its own design.

On the lower main LA2 there is a power plant 5 with electric drives, a backup energy source 6. In contrast to the first option in this case, the upper LA1 not only generates useful electric energy and transfers it to the main LA, but also creates additional resistance, which must be compensated by the power plant 5 main lower LA2. To determine under what conditions the energy balance of such interaction can be positive, it is necessary to calculate the entire system on the basis of the general available technical and statistical data for the given wind conditions of the proposed area of operation of the system.

The above two possible options for creating a bunch of aircraft capable of holding a payload for a long time at a given point do not exclude other options for implementing this system. Perhaps a more complex spatial movement of two aircraft connected by a cable, capable of sharing the energy of the speed difference of wind flows, without energy exchange through a cable-cable.

The launch and rise to the height of such a system can be carried out depending on which aircraft are included in the bundle. For example, to implement the first option described above, the start of the system can be carried out similarly to the launch of a high-altitude balloon. LA2 - controlled parachute system - is in the assembled state and is mounted on the suspension to the balloon at the time of launch. The cable is also fixed to the balloon in the state wound by an automatic winch.

After the aerostatic system reaches the height set for LA1, the winch begins to unwind, lowering the container with the parachute system into the lower atmosphere to the required height for LA2. At this height, the canopy of the guided parachute system is automatically opened. After that, the control system of the entire ligament using the controls will balance the system in the atmosphere according to the intensity of the wind flows, as shown in Fig.3.

The parachute system must have a sling system that allows both to reduce the effective area of the dome in the required range, and to change the direction of the created resistance force. The balloon should also have horizontal and vertical rudders, allowing it to adjust its position in the atmosphere.

For the second embodiment of the invention, an aircraft-type aircraft is used, the launch of the ligament is carried out from an aerodrome having a runway corresponding to the flight performance of the aircraft ligament. The launch is carried out similarly to the take-off scheme for an aircraft - towing and glider. The cable should be on the winch on LA1 or LA2. Before the start, it is unwound to the necessary length for take-off and fixed on another aircraft.

On the LA2 tugboat, during take-off and climb, an additional energy source is placed, which allows the ligament to fly up and gain the necessary height. After gaining a bunch of heights necessary for LA1, the automatic winch unwinds the cable, and LA2 is reduced to the height set for it. Then start the wind generator, placed on LA1, balance and orient the bunch in the atmosphere, respectively, flight mission and wind conditions (figure 4).

We will perform a preliminary calculation of the first version of the system, when two aircraft connected by a cable are balanced in space only due to aerodynamic forces (LA1 - tethered balloon, LA2 - parachute system). The ligament is stationary relative to the Earth (Fig. 5). We have two air currents moving in opposite directions with approximately equal speeds. Between them is the boundary region of the minimum wind speed relative to the Earth. We arbitrarily take a point of zero relative velocity at an altitude of H = 20 km. Up and down from this point, the wind speed increases in opposite directions. The maximum height difference ΔH to the upper and lower aircrafts is 4 km or ± 2 km from the point V _n = 0, at H = 20 km, and the length of the cable harness L _mp ~ 4,5 ÷ 6 km. The wind speed varies from V _n = 0 to V _n = 5 ÷ 25 m / s according to a parabolic law depending on the height. The upper LA1 carries the mass of the cable ∑G _Tr and the mass of the payload G _Mon Lower LA2 should create an equivalent cable tension, i.e. resistance force X _LA2 , which will balance the resistance force of the upper LA1 - X _LA1 . If necessary, LA1 can carry part of the payload. A diagram of the forces acting on the ligament is also shown in FIG.

We compose the equations describing the system in equilibrium:

where X _LA1 , X _LA2 , R _mpX and Y _LA1 , Y _LA2 , R _mpY are the projections of the resulting aerodynamic forces on the axis OX, OY, G _LA1 , G _LA2 , G _mp is the weight of the aircraft and the total weight of the cable, ∑M _mp is the total aerodynamic moment of the cable, ∑M _i - moments of other forces acting on the system relative to the application center ∑R _mp , total aerodynamic force acting on the cable, Ф _ЛА1 - aerostatic lifting force, if LA1 is an aerostatic aircraft.

The solution of such a system of equations requires determining the geometric parameters of the cable, its position in space and the aerodynamic force acting on the cable when it flows around a wind stream of different strength and direction. Therefore, in a first approximation, this problem is solved by dividing the cable into elementary sections and finding a solution for each section separately, starting from the upper point of the cable (LA1) to the lower point (LA2). In solving this problem, we assume that all forces are located in the same XOY plane. In reality, the air flows can have any velocity vector and the tethered cable will have an offset along the OZ axis, but at this stage it is important to determine the balance of forces and the area of possible existence of such a system.

For calculations, we used the known data on cable cables from Kevlar (breaking length 42 km), the specific gravity of the aerostatic apparatus structure is 40% of G _LA1 .

The calculation of the position of the cable in space showed that for a given range of wind flow speeds from 0 to 20 m / s, the horizontal deviations of LA1 and LA2 (X axis, Fig. 5) will be about 250 m with a difference in height between LA1 and LA2 of 4 km . The aerodynamic drag of a cable with a given range of wind flow velocities does not significantly affect the position of the aircraft.

The weight calculation of the system showed that for these calculated wind and altitude conditions, the required volume of the aerostatic shell LA1 will be 50370 m ³ , the total take-off weight of the LA bunch (high-altitude platform) is 2560 kg for a given payload weight of 500 kg. According to the weight and size parameters, the high-altitude platform - the LA aircraft has the advantage of 3-5 times in comparison with high-altitude airships powered by solar energy. This indicator allows us to conclude that it is economically feasible to implement the proposed idea of a high-altitude platform.

The invention can be used to create a high-altitude stratospheric platform designed to lift the payload to a height of 15 ÷ 25 km (the height of the bicycle pause and tropopause) and capable of being at a given point from several months to a year or more. It is possible to use the present invention at lower altitudes if there is a necessary difference in the speed and direction of air flows.

Creating a high-altitude platform with a duration of barrage of one month to a year or more above a given point on the surface of the earth, including northern latitudes (up to 75 ° N), while maintaining a low cost of the system itself and the cost of its life cycle compared with satellite systems, is capable of provide significant competitive advantage.

Claims (4)

1. The method of placing a high-altitude platform, consisting of a bunch of aircraft (LA), which consists in lifting the platform to a predetermined height, supplying energy and holding it at a given point, characterized in that the aircraft are placed in stable wind currents moving at different speeds relative to the ground and (or) in a different direction, and holding this ligament at a given point or moving it relative to the ground in a given direction is provided by aerodynamic controls and power the probe of several aircraft of the ligament, using the energy difference between the wind flows while maintaining a constant flight altitude, and (or) due to the energy received from a wind generator installed on one of the aircraft of the ligament, and transmitted through a cable-cable to the power plants of other (other) aircraft, moreover, the payload is placed either on aircraft, or on a cable cable connecting the aircraft. 2. A high-altitude platform, including a bunch of several aircraft equipped with aerodynamic controls, an automatic control system and power plants, interconnected by means of a flexible cable cable that provides power transmission and contains electric power transmission channels and an information control signal from one device to another , characterized in that the platform contains in conjunction any type of aircraft, moreover, on one of the aircraft ligaments installed in the generator. 3. High-altitude platform, including a bunch of several aircraft according to claim 2, characterized in that the bunch includes aircraft of the same types. 4. High-altitude platform, including a bunch of several aircraft according to claim 2, characterized in that the bunch includes aircraft of various types.

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