JP2012025349A - Flying object, system and method for flying - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a flying object that can be miniaturized without the need for an external supply of electric power, and to provide a system and method for flying.SOLUTION: The flying object 100 includes: a body 110; a propeller for propelling the body 110 in a travelling direction; a solar cell film that is a film-shaped solar cell; and a storage unit for storing the solar cell film while connecting one end of the solar cell film. The body 110 includes: a storage driver 188 for driving the storage unit to develop the solar cell film from the storage unit backward in the travelling direction, while the one end of the solar cell film is connected to the storage unit; an energy storage unit 170 for storing the electric power generated by the solar cell film; and a propeller driver 184 for driving the propeller by the use of the electric power generated by the solar cell film or the electric power stored in the energy storage unit 170.

Description

  The present invention relates to a flying object, a flying system, and a flying method.

  In recent years, development of a wireless communication network using a flying object that can always stay in the stratosphere has been advanced. Since the stratosphere is higher than the summit, if a flying object always stays in the stratosphere, it is possible to cover many wireless communication areas while reducing the number of wireless communication relay devices. In addition, since the stratosphere is much lower than satellites, if a flying object always stays in the stratosphere, wireless communications can be easily relayed to electronic devices with low transmission power such as mobile phones. .

  For example, in Patent Document 1, by providing a solar panel on the upper surface of the wing, the stratosphere platform is driven by the power obtained by the solar panel during the day, and the stratosphere platform is driven by the power transmitted from the power transmission device at night. Techniques for making them disclosed are disclosed.

  However, the technique disclosed in Patent Document 1 requires a power transmission device that supplies power to the flying object in order to make the flying object stay in the stratosphere. In addition, if the electric power obtained by the solar cell installed in the flying object is stored to replace the electric power necessary for night flight, a large amount of solar cell is required and the flying object needs to be enlarged. When the body is enlarged, it is necessary to ensure rigidity and toughness that do not decompose due to air disturbance, and problems such as high costs arise.

  The present invention has been made in view of the above circumstances, and an object of the present invention is to provide a flying object, a flying system, and a flying method that can be reduced in size without requiring supply of electric power from the outside.

  In order to solve the above-described problems and achieve the object, a flying object according to one aspect of the present invention is a flying object, a main body part, a propulsion part that propels the main body part in a traveling direction, and a film shape A solar cell film that is a solar cell, and a storage unit that stores the solar cell film in a state where one end of the solar cell film is connected, the main body unit driving the storage unit, and the solar cell film With one end connected to the storage unit, a storage drive unit that expands the solar cell film from the storage unit to the rear in the traveling direction, a power storage unit that stores electric power generated by the solar cell film, A propulsion drive unit that drives the propulsion unit using electric power generated by the solar cell film or electric power stored in the power storage unit.

  Further, a flying system according to another aspect of the present invention is a flying system including a first flying body and a second flying body that are the above-mentioned flying bodies, wherein the second flying body is made of the solar cell film. A second main body connected to the other end; and a second propulsion unit for propelling the second main body in the direction of travel, wherein the second main body generates electric power generated by the solar cell film. A second power storage unit that stores power, and a second propulsion drive unit that drives the second propulsion unit using power generated by the solar cell film or power stored in the second power storage unit. It is characterized by.

  Further, a flight method according to another aspect of the present invention is a flight method of a flying object, wherein the flying object includes a main body part, a propulsion part that propels the main body part in a traveling direction, and a film-like solar cell. A solar cell film, and a storage unit that stores the solar cell film in a state where one end of the solar cell film is connected, a storage drive unit driving the storage unit, and the one end of the solar cell film is the A storage drive step for expanding the solar cell film from the storage unit to the rear in the traveling direction in a state connected to the storage unit, and a power storage step for storing the electric power generated by the solar cell film by the power storage unit. The propulsion drive unit includes the propulsion drive step of driving the propulsion unit using the electric power generated by the solar cell film or the electric power stored by the electric storage step. And butterflies.

  According to the present invention, there is an effect that it is possible to reduce the size without requiring supply of electric power from the outside.

FIG. 1 is a plan view showing an example of a state of the flying body of the first embodiment before the development of the solar cell film. FIG. 2 is a plan view showing a state example of the flying object according to the first embodiment after the solar cell film is developed. FIG. 3 is a longitudinal sectional view showing an example of the storage unit of the flying object of the first embodiment. FIG. 4 is a block diagram illustrating a functional configuration example of the flying object according to the first embodiment. FIG. 5 is a flowchart showing a flight operation example performed by the flying object of the first embodiment. FIG. 6 is a plan view showing an example of a state before the solar cell film is deployed in the flight system of the second embodiment. FIG. 7 is a plan view showing an example of a state after the solar cell film of the flight system of the second embodiment is developed. FIG. 8 is a side view showing an example of a flight posture after the solar cell film is deployed in the flight system of the second embodiment. FIG. 9 is a diagram illustrating an example of the light detection unit provided on the upper surface of the main body of the first flying object according to the second embodiment. FIG. 10 is a block diagram illustrating a functional configuration example of the first flying object according to the second embodiment. FIG. 11 is a block diagram illustrating a functional configuration example of the second flying object according to the second embodiment. FIG. 12 is a flowchart showing an example of a replacement operation with a spare aircraft performed in the flight system of the second embodiment.

  Hereinafter, embodiments of a flying object, a flying system, and a flying method according to the present invention will be described in detail with reference to the accompanying drawings. In each of the following embodiments, a case where the flying object is used as a relay station for terrestrial digital television broadcasting by always staying in the stratosphere will be described as an example. However, the present invention is not limited to this. The flying bodies of the following embodiments can be used as relay stations for radio wave devices such as mobile phones or radio broadcasts by always staying in the stratosphere.

(First embodiment)
First, the configuration of the flying object of the first embodiment will be described.

  FIG. 1 is a plan view showing an example of a state before the solar cell film of the flying body 100 according to the first embodiment, and FIG. 2 shows a state after the solar cell film 150 of the flying body 100 according to the first embodiment is deployed. It is a top view which shows an example. As shown in FIGS. 1 and 2, the flying object 100 includes a main body part 110, a solar battery 114, a propeller 120, a connecting part 130, a storage part 140, and a solar battery film 150.

  The main body 110 has a wing-surface-heavy aircraft structure close to that of a normal propeller airplane, and has a structure that is resistant to destruction caused by atmospheric turbulence that rises from the ground surface through the troposphere. A solar cell 114 is attached to the upper surface of the main wing 112 of the main body 110.

  The propeller 120 (an example of a propulsion unit) is configured to propel the main body 110 in the traveling direction, and is disposed in front of the main body 110 in the traveling direction in the first embodiment. The propeller 120 of the first embodiment is a towed propeller.

  The connecting unit 130 connects the main body unit 110 and the storage unit 140. In the first embodiment, the connecting part 130 is installed behind the main body part 110 in the moving direction, and connects the storage part 140 behind the main body part 110 in the moving direction.

  The solar cell film 150 is a low-rigidity film-like solar cell, and a flexible film type is used in the first embodiment.

  The storage unit 140 stores the solar cell film 150 with one end thereof connected. FIG. 3 is a vertical cross-sectional view (a cross-sectional view in the plan view of FIG. 1) showing an example of the storage unit 140 of the flying object 100 of the first embodiment. As shown in FIGS. 1 and 3, the storage unit 140 is a cylindrical case, and a winding core 141 is provided at the center thereof. The storage unit 140 stores the solar cell film 150 wound around the core 141. One end of the solar cell film 150 is connected to the winding core 141, and the other end of the solar cell film 150 can be discharged from the discharge port 142 to the outside of the storage unit 140.

  In the state shown in FIG. 1, the storage unit 140 rotates the winding core 141 clockwise (clockwise in the longitudinal sectional view of FIG. 3) when the flying object 100 reaches a predetermined altitude of the stratosphere. The solar cell film 150 is discharged. Thus, in 1st Embodiment, since the solar cell film 150 is discharged | emitted behind the advancing direction of the main-body part 110, the flying body 100 will be in the state which pulls the discharged | emitted solar cell film 150. FIG. Therefore, as shown in FIG. 2, the solar cell film 150 is unfolded backward in the traveling direction of the main body 110 by receiving wind due to air speed. In the state shown in FIG. 2, the storage unit 140 rotates the winding core 141 counterclockwise (counterclockwise in the longitudinal sectional view of FIG. 3) when the flying object 100 deviates from the predetermined altitude of the stratosphere. The battery film 150 is wound up, and the solar cell film 150 is stored in the storage unit 140 as shown in FIG.

  In addition, although 1st Embodiment demonstrated the example which winds up the solar cell film 150 and stores it in the storage part 140, the storage system of the solar cell film 150 is not limited to this, For example, the solar cell film 150 May be folded and stored in the storage unit 140.

  FIG. 4 is a block diagram illustrating an example of a functional configuration of the flying object 100 according to the first embodiment. As shown in FIG. 4, the main body 110 of the flying object 100 includes a power storage unit 170, a power control unit 180, a steering unit 182, a propulsion drive unit 184, a position detection unit 186, a storage drive unit 188, A wireless communication unit 190 and a main control unit 192 are provided.

  The power storage unit 170 stores the power generated by the solar cell 114 and the solar cell film 150, and can be realized by, for example, a storage battery.

  The power control unit 180 stabilizes the power generated by the solar cell 114 and the solar cell film 150 and causes the power storage unit 170 to store (charge) the power. In addition, the power control unit 180 supplies the stabilized power or the power stored in the power storage unit 170 to the steering unit 182, the propulsion drive unit 184, the position detection unit 186, the storage drive unit 188, the wireless communication unit 190, and It is supplied to the main control unit 192 and the like. Specifically, the power control unit 180 supplies the stabilized power generated by the solar cell 114 and the solar cell film 150 to each unit described above during the daytime when the sun is out, and the sun is out. At night when there is no power, the power stored in the power storage unit 170 is supplied to each unit described above.

  The steering unit 182 controls the traveling direction of the main body unit 110.

  The propulsion drive unit 184 is a drive source of the propeller 120 and can be realized by, for example, a motor. The propulsion drive unit 184 receives the control of the main control unit 192 and drives the propeller 120 using the power generated by the solar cell 114 and the solar cell film 150 or the power stored in the power storage unit 170.

  The position detector 186 detects the position including the altitude of the main body 110 and can be realized by a GPS sensor, a barometer, or the like.

  The storage drive unit 188 is a drive source of the storage unit 140 and can be realized by, for example, a motor. The storage drive unit 188 is controlled by the main control unit 192 to drive the storage unit 140 using the power generated by the solar cell 114 or the solar cell film 150 or the power stored in the power storage unit 170. Thereby, the storage drive unit 188 expands the solar cell film 150 from the storage unit 140 to the rear in the traveling direction with one end of the solar cell film 150 connected to the storage unit 140, or the expanded solar cell film. 150 is stored in the storage unit 140.

  The wireless communication unit 190 receives radio waves of terrestrial digital television broadcasting from a broadcasting station (not shown) on the ground and transmits the radio waves to a predetermined area on the ground. A receiving antenna, a receiver, a controller, a transmitter, This is realized by a transmission antenna or the like. In addition, since the flying object 100 needs to perform turning etc. while staying at the same place of the predetermined altitude of the stratosphere, the directivity of the transmitting antenna is variably controlled in real time according to the flying posture of the flying object 100 by the controller. The As a result, it is possible to prevent radio waves from reaching unintended ground areas and prevent radio waves from reaching necessary ground areas.

  The main control unit 192 controls each unit of the flying object 100 and can be realized by an existing control device such as a CPU (Central Processing Unit). For example, when the main control unit 192 determines that the position detected by the position detection unit 186 has reached a predetermined height in the stratosphere, the main control unit 192 causes the storage drive unit 188 to deploy the solar cell film 150 from the storage unit 140. Take control. Similarly, when the main control unit 192 determines that the position detected by the position detection unit 186 is out of the predetermined altitude of the stratosphere, the main control unit 192 causes the storage drive unit 188 to store the solar cell film 150 in the storage unit 140. Control.

  Next, the operation of the flying object of the first embodiment will be described.

  FIG. 5 is a flowchart illustrating an example of a flight operation performed by the flying object 100 according to the first embodiment. Since large energy is required to raise the flying object 100 to a predetermined altitude in the stratosphere, in the first embodiment, the aircraft 100 is pulled up by another airplane (not shown) until it passes through the troposphere. To do. The power storage unit 170 of the flying object 100 is also fully charged on the ground in advance so that driving energy such as ascent can be obtained. Specifically, the flying object 100 is pulled by another airplane until the altitude reaches about 15 km, and when the altitude reaches about 15 km, the flying object 100 is separated from the other airplanes and starts flying by the flying object 100 itself. In FIG. 5, the flight operation of the flying object 100 after this will be described. Note that the flying operation of the flying object 100 described in FIG. 5 is performed during the day when the electric power from sunlight is available.

  First, the propulsion drive unit 184 drives the propeller 120 to raise the flying object 100 in the traveling direction controlled by the steering unit 182 (step S100).

  Subsequently, the main control unit 192 determines whether or not the position detected by the position detection unit 186 has reached an altitude of 20 km, which is a predetermined altitude in the stratosphere (step S102).

  If the main control unit 192 determines that the predetermined altitude of 20 km has not been reached (No in step S102), the process returns to step S100 and continues to raise the flying object 100.

  On the other hand, when it is determined by the main control unit 192 that the altitude of 20 km has been reached (Yes in step S102), the storage drive unit 188 drives the storage unit 140, thereby the solar cell film 150. Is expanded from the storage unit 140 (step S104).

  Subsequently, the steering unit 182 controls the traveling direction so that the flying object 100 stays at a predetermined altitude in the stratosphere (step S106).

  If the main control unit 192 determines that the position detected by the position detection unit 186 is out of the predetermined altitude of the stratosphere, such as when returning the flying object 100 to the ground, the storage drive unit 188 stores the The developed solar cell film 150 is stored in the storage unit 140 by driving the unit 140.

  As described above, the flying object 100 of the first embodiment includes only the solar battery 114 of the amount that can be provided in the main body 110 among the solar batteries that generate electric power necessary for the flight of the flying object 100 and the like. The remaining portion is developed and pulled behind the flying body 100 in the traveling direction using the solar cell film 150. Therefore, according to the flying object 100 of 1st Embodiment, it can reduce in size, without requiring supply of electric power from the outside.

(Second Embodiment)
In the second embodiment, a flying system using two flying bodies will be described. In the following, differences from the first embodiment will be mainly described, and components having the same functions as those in the first embodiment will be given the same names and symbols as those in the first embodiment, and description thereof will be given. Is omitted.

  First, the structure of the flight system of 2nd Embodiment is demonstrated.

  FIG. 6 is a plan view illustrating an example of the flight system 1000 according to the second embodiment before the solar cell film is deployed. FIG. 7 is a plan view showing an example of a state after the solar cell film 150 is deployed in the flight system 1000 of the second embodiment. FIG. 8 is a side view showing an example of the flight posture after the solar cell film 150 is deployed in the flight system 1000 of the second embodiment. FIG. 9 is a diagram illustrating an example of the light detection unit 1196 provided on the upper surface of the main body 1110 of the first flying object 1100 of the second embodiment. As shown in FIGS. 6 to 8, the flying system 1000 includes a first flying body 1100 and a second flying body 1200.

  The first flying object 1100 is the same as the flying object 100 of the first embodiment except that the light detection unit 1196 is provided on the upper surface of the main body part 1110 and the functional configuration of the main body part 1110. The differences from the flying object 100 of the first embodiment will be described later.

  The second flying object 1200 includes a main body part 1210, a solar battery 1214, a propeller 1220, and a connecting part 1230.

  The main body 1210 (an example of the second main body) has the same structure as the flying body 100 of the first embodiment, and a solar cell 1214 is attached to the upper surface of the main wing 1212 of the main body 1210. The generated power of the solar cell 1214 is 2 kw at the maximum, and the solar cell 114 is the same.

  The propeller 1220 (an example of a second propulsion unit) is configured to propel the main body portion 1210 in the traveling direction, and is disposed behind the main body portion 1210 in the traveling direction. The propeller 1220 is a propulsion type propeller.

  The connection part 1230 connects the main-body part 1210 and the other end of the solar cell film 150 stored in the storage part 140 of the first flying object 1100. The connecting part 1230 is installed in front of the main body part 1210 in the traveling direction, and connects the other end of the solar cell film 150 in front of the main body part 1210 in the moving direction.

  In the second embodiment, the propeller 1220 of the second flying object 1200 is a propulsion type propeller, and is disposed behind the main body part 1210 of the second flying object 1200. There is no interference with the solar cell film 150 disposed in the forward direction.

  In the second embodiment, when the solar cell film 150 is discharged from the storage unit 140 of the first flying object 1100 to the rear in the traveling direction of the main body part 1110, the second flying object 1200 weakens the propulsion force of the propeller 1220, The solar cell film 150 is pulled backward in the traveling direction by making the speed slightly slower than that of the first flying object 1100. Thereby, a tension is applied to the solar cell film 150, and the solar cell film 150 is developed as shown in FIG. The second flying object 1200 returns the propulsion force of the propeller 1220 to the same speed as the first flying object 1100 after the solar cell film 150 is deployed. The second flying object 1200 maintains an appropriate unfolded state so as to receive sunlight by adjusting the driving force of the propeller 1220 to adjust the tension applied to the solar cell film 150.

  The solar cell film 150 has a width of 12 m, a length of 200 m, and a thickness of 50 microns. The solar cell film 150 is a thin-film solar cell formed on a base film made of aramid fibers. In the second embodiment, the deployed solar cell film 150 receives a large amount of wind force, and therefore, a tape 1152 for reinforcing rigidity is disposed at the end of the solar cell film 150. Specifically, a tape 1152 having a width of 50 cm is disposed at the end of the surface opposite to the surface irradiated with sunlight. Thereby, the solar cell film 150 is configured to withstand a large tension.

  The solar cell film 150 having an area of 2400 square meters has an ideal maximum output of about 240 kW when irradiated with sunlight at right angles, but in the state where it is pulled by the first flying object 1100 and the second flying object 1200, Because it is similar to the foot, it is difficult to always keep it perpendicular to the light. Therefore, the average output when the sun is directly above is about 180 kW.

  In the second embodiment, when the solar cell film 150 is deployed from the storage unit 140 of the first flying object 1100, the flying system 1000 increases the altitude of the second flying object 1200 to the first flying object as shown in FIG. Fly below the altitude of the body 1100. This is a flight posture that utilizes the fact that the solar cell film 150 receives the greatest air resistance and lift in the flight system 1000, and is upward when the altitude of the first flying object 1100 is higher than that of the second flying object 1200. The lift can be obtained. In addition, the flight altitude of the flight system 1000 can be changed by changing the altitude difference between the first flying object 1100 and the second flying object 1200, and the solar cell film 150 can function as an elevator. For example, as shown in FIG. 8, when the altitude of the first flying object 1100 ahead in the traveling direction is higher than the second flying object 1200 behind the traveling direction, the flying system 1000 receives a large lift and can therefore be raised. it can.

  FIG. 10 is a block diagram illustrating an example of a functional configuration of the first flying object 1100 of the flying system 1000 according to the second embodiment. The first flying object 1100 is different from the flying object 100 of the first embodiment in that it includes a light detection unit 1196 and various sensors 1191 and the control contents of the steering unit 1182 and the main control unit 1192.

  As shown in FIG. 9, the light detection unit 1196 includes a plurality of light detection sensors 1196 </ b> A to 1196 </ b> C that detect light (sunlight) at different angles, and light detection provided in the light detection unit 1196. The position of the sun is detected from the amount of light detected by the sensors 1196A to 1196C. Specifically, the light detection unit 1196 detects that the sun is positioned in the direction of the light detection sensor having the largest amount of light detected among the light detection sensors 1196A to 1196C.

  The steering unit 1182 controls the inclination of the main body part 1110 so that the main body part 1110 is positioned perpendicular to the position of the sun detected by the light detection part 1196. For example, even when the morning and evening sun is in a tilted position, the solar cell film 150 is angled to control so that the sunlight and the solar cell film 150 approach each other vertically. Thereby, the perpendicularity with respect to the sunlight of the solar cell film 150 can be corrected according to the inclination of the sun, and the output of the solar cell film 150 can be increased. In this case, since the altitude of the flying system 1000 is raised or lowered by the force received by the solar cell film 150, the altitudes of the first flying body 1100 and the second flying body 1200 are appropriately reversed to zigzag with respect to the target altitude. Will be changed.

  The various sensors 1191 are sensors that detect airspeed, humidity, acceleration, sunlight, and the like, and can be realized by, for example, a Pitot tube.

  The main control unit 1192 (an example of a calculation unit and a notification unit) calculates the wind conditions based on the detection results of the various sensors 1191, and if the calculated wind conditions satisfy a predetermined condition, notifies the spare machine to that effect. . Thereby, the flight system 1000 can be replaced with a spare machine.

  FIG. 11 is a block diagram illustrating an example of a functional configuration of the second flying object 1200 of the flying system 1000 according to the second embodiment. As shown in FIG. 11, the main body 1210 of the second flying object 1200 includes a power storage unit 1270, a power control unit 1280, a steering unit 1282, a propulsion drive unit 1284, a position detection unit 1286, and a date / time data storage unit. 1288, a wireless communication unit 1290, various sensors 1291, and a main control unit 1292.

  The power storage unit 1270 stores power generated by the solar battery 1214 and the solar battery film 150, and can be realized by, for example, a storage battery.

  The power control unit 1280 stabilizes the power generated by the solar cell 1214 and the solar cell film 150 and causes the power storage unit 1270 to store (charge) the power. In addition, the power control unit 1280 supplies the stabilized power or the power stored in the power storage unit 1270 to the steering unit 1282, the propulsion drive unit 1284, the position detection unit 1286, the date / time data storage unit 1288, the wireless communication unit 1290, It is supplied to various sensors 1291, the main control unit 1292, and the like. Specifically, the power control unit 1280 supplies the electric power generated and stabilized by the solar cell 1214 and the solar cell film 150 to each unit described above during the daytime when the sun is out, and the sun is out. At night when there is no power, the power stored in the power storage unit 1270 is supplied to each unit described above.

  The propulsion drive unit 1284 (an example of the second propulsion drive unit) is a drive source of the propeller 1220, and can be realized by, for example, a motor. The propulsion drive unit 1284 receives the control of the main control unit 1292 and drives the propeller 1220 using the power generated by the solar cell 1214 and the solar cell film 150 or the power stored in the power storage unit 1270.

  The propulsion drive unit 1284 reduces the driving force of the propeller 1220 when the storage unit 140 is driven by the first flying object 1100 and the solar cell film 150 is discharged backward in the traveling direction, and the second flying object 1200 The speed is made slower than the speed of the first flying object 1100. As a result, the second flying object 1200 pulls the solar cell film 150 backward in the traveling direction, tension is applied to the solar cell film 150, and it is deployed as shown in FIG. The propulsion drive unit 1284 restores the driving force of the propeller 1220 after the solar cell film 150 is deployed, and sets the speed of the second flying object 1200 to the same speed as that of the first flying object 1100.

  Since the position detection unit 1286 and the wireless communication unit 1290 are the same as the position detection unit 186 and the wireless communication unit 190 of the flying object 100 according to the first embodiment, description thereof will be omitted. Also, the various sensors 1291 are the same as the various sensors 1191 of the first flying object 1100, and thus the description thereof is omitted.

  The date / time data storage unit 1288 updates and stores the current date / time data.

  The steering part 1282 (an example of a second steering part) controls the traveling direction of the main body part 1210. When the solar cell film 150 is deployed, the steering part 1282 controls the traveling direction of the main body part 1210, and FIG. As shown, the altitude of the second flying object 1200 is made lower than the altitude of the first flying object 1100. Specifically, the steering unit 1282 performs the second flight according to the position of the main body 1210 detected by the position detection unit 1286 and the absolute sun position based on the current date / time data stored in the date / time data storage unit 1288. Control the altitude of the body 1200. Thereby, the perpendicularity with respect to the sunlight of the solar cell film 150 can be corrected according to the inclination of the sun.

  The main control unit 1292 controls each unit of the second flying object 1200 and can be realized by an existing control device such as a CPU (Central Processing Unit). For example, the main control unit 1292 receives a notification that the solar cell film 150 has been discharged rearward in the traveling direction from the first flying object 1100, and controls the propulsion drive unit 1284 and the steering unit 1282. The main control unit 1292 calculates the absolute solar position using the position of the main body 1210 detected by the position detection unit 1286 and the current date / time data stored in the date / time data storage unit 1288.

  Note that in the wireless communication unit 1290, the broadcast wave transmission output is 5 W per channel, and the transmitter is provided for 10 channels. The power consumption of the transmitter is about 300 W continuously, and the power consumption of the entire wireless communication unit 1290 is less than 500 W. Further, the power consumption of the propulsion drive unit 1284 and the propeller 1220 is a maximum of 30 kW, and the second flying object 1200 flies with an average power consumption of about 10 kW. The power storage unit 1270 has an output capacity of 200 kWh and can drive the propeller 1220 for about 10 hours. Note that the mass of the power storage unit 1270 is about 1 ton. Also, during the day, when the wind speed is temporarily strong due to weather conditions, the power generated by the solar cell 1214 and the solar cell film 150 and the output of the power stored in the power storage unit 1270 are added together to add the propeller 1220 The driving force is increased to cause the second flying object 1200 to fly and be prevented from being swept away. The same applies to the first flying object 1100.

  Next, the operation of the flight system of the second embodiment will be described.

  Note that the basic flow of the flight operation of the flight system 1000 is substantially the same as the flight operation of the flying object 100 of the first embodiment described with reference to the flowchart of FIG.

  Like the flying object 100 of the first embodiment, the flying system 1000 of the second embodiment is lifted by being pulled by another airplane (not shown) until it exits the troposphere.

  Then, the control of step S100 in the flowchart of FIG. 5 is performed by the first flying object 1100 and the second flying object 1200, the control of steps S102 to S104 is performed by the first flying object 1100, and the control of step S106 is performed by the second flying object. 1200 does. In step S104, the propulsion drive unit 1284 of the second flying object 1200 temporarily reduces the driving force of the propeller 1220 so that the speed of the second flying object 1200 is temporarily higher than the speed of the first flying object 1100. In addition, the steering unit 1282 of the second flying object 1200 controls the traveling direction of the main body part 1210 to make the altitude of the second flying object 1200 lower than the altitude of the first flying object 1100.

  Here, the reason why the predetermined altitude of the stratosphere where the flight system 1000 stays is set to an altitude of 20 km will be described. First, since the flight system 1000 flies by driving a propeller with electric power derived from a solar cell or a storage battery, there is a problem that when the atmosphere becomes thin, driving force and lift cannot be obtained.

  For this reason, the higher the altitude, the longer the line-of-sight distance and the better the environment for radio wave transmission. However, due to the relationship between driving force and lift, the flight system 1000 is limited to an altitude of about 30 to 35 km, and the altitude is 40 km. Altitude cannot be maintained in areas that exceed this range.

  In addition, in the troposphere at an altitude of 10 km or less, there is a high possibility of encountering severe atmospheric turbulence, and when the atmospheric turbulence is encountered, strong stress acts on the solar cell film 150 and the flight system 1000 may be destroyed. Furthermore, in the troposphere at an altitude of 10 km or less, there are many clouds, which may make flight impossible due to insufficient power. Moreover, the altitude of 12 km or less overlaps with an airspace where a normal airplane such as a passenger plane flies, and the flight system 1000 cannot stay.

  From the above viewpoint, the altitude at which the flying system 1000 stays is suitable for an altitude of 13 km to 30 km, and in the second embodiment, the altitude is 20 km.

  When the flight system 1000 stays at an altitude of 20 km, the terrestrial television transmission station can cover an area with a radius of 100 km or more. For example, the flight system 1000 stays in the vicinity of 20 km above the center of Tokyo and performs digital terrestrial television broadcasting. Cover all Kanto prefectures, western Shizuoka prefecture, Nagano prefecture, and western Fukushima prefecture.

  In addition, when deploying throughout Japan, it is possible to cover the entire country including remote islands by flying about 10 flight systems 1000. As a result, it is possible to aggregate several hundreds of television relay stations nationwide and reduce the cost of the broadcasting system.

  Note that the flight system 1000 of the second embodiment is operated in two sets with a standby system (not shown) in preparation for a failure. The flying system 1000 is arranged at a fixed position, and the spare machine waits at a position on the windward side of about 20 km depending on the wind direction at that time. If the flight system 1000 is likely to break down, be blown by the wind, or crashed, notify the spare machine to that effect, and move the spare machine to a fixed position and continue operation as a relay station Can do. Also, in preparation for cases where replacement with a spare aircraft is not possible, prepare a normal jet-propelled high altitude aircraft equipped with a wireless communication unit similar to the flight system 1000. You may make it back up and perform backup.

  FIG. 12 is a flowchart illustrating an example of a replacement operation with a spare aircraft performed in the flight system 1000 according to the second embodiment.

  First, the position detector 186 of the first flying object 1100 senses the position of the first flying object 1100 (step S200).

  Subsequently, the main control unit 1192 of the first flying object 1100 calculates the ground movement vector Vg of the first flying object 1100 (step S202).

  Subsequently, various sensors 1191 such as a Pitot tube of the first flying object 1100 perform flow velocity sensing around the first flying object 1100 (step S204).

  Subsequently, the main control unit 1192 calculates the air movement vector Va of the first flying object 1100 (step S206).

  Subsequently, the main control unit 1192 calculates Vw = Vg−Va (step S208).

  Subsequently, the main control unit 1192 calculates || Vg ||, || Va ||, || Vw || = || Vg ||-| Va || (Step S210).

  Subsequently, the main control unit 1192 uses Vw and || Vw || to derive the wind conditions around the first flying object 1100 (wind direction and wind speed information around the first flying object 1100) (step S212).

  Subsequently, the main control unit 1192 calculates the flight angle and the PV power generation amount with respect to the upwind direction of the wind conditions around the first flying object 1100 (step S214).

  Subsequently, the main control unit 1192 acquires the propeller operation thrust information based on the PV power generation amount and the remaining power storage amount (step S216).

  Subsequently, the main control unit 1192 calculates the operable airspeed Vp of the first flying object 1100 based on the propeller operational thrust information and the payload information (step S218).

  Subsequently, if ∫Vpdt−∫ || Vw || dt> 0 for t1 to t2 is satisfied (Yes in step S220), the main control unit 1192 continues to fly the first flying object 1100 (flying system 1000). (Step S222), if ∫Vpdt−∫ || Vw || dt> 0 for t1 to t2 does not hold (No in Step S220), a spare machine (not shown) is notified of replacement (Step S224).

  As described above, the flight system 1000 according to the second embodiment has an amount of solar that can be provided in the main body 1110 of the first flying body 1100 among the solar cells that generate electric power necessary for the flight of the flying system 1000 and the like. Only the battery 114 is affixed to the main wing 112, and only an amount of solar cell 1214 that can be provided in the main body 1210 of the second flying object 1200 is affixed to the main wing 1212. Then, the rest is suspended by the first flying object 1100 and the second flying object 1200 using the solar cell film 150. Therefore, according to the flight system 1000 of the second embodiment, it is possible to reduce the size without requiring supply of electric power from the outside.

(Modification)
In addition, this invention is not limited to the said embodiment, A various deformation | transformation is possible. For example, in the flying system 1000 of the second embodiment, the control contents and configuration of the first flying object 1100 may be the control contents and structure of the second flying object 1200, and the control contents and configuration of the second flying object 1200 may be the same. The control content and configuration of the first flying object 1100 may be used. That is, the control content and configuration of the first flying object 1100 and the second flying object 1200 can be appropriately switched.

100, 1100 flying object (first flying object)
DESCRIPTION OF SYMBOLS 110, 1110 Main body part 112 Main wing 114 Solar cell 120 Propeller 130 Connection part 140 Storage part 141 Winding core 142 Outlet 150 Solar cell film 170 Power storage part 180 Power control part 182, 1182 Steering part 184 Propulsion drive part 186 Position detection part 188 Storage Drive unit 190 Wireless communication unit 192, 1192 Main control unit 1191 Various sensors 1196 Photodetection unit 1196A to 1196C Photodetection sensor 1200 Second projectile body 1210 Main body unit 1212 Main wing 1214 Solar cell 1220 Propeller 1230 Connection unit 1270 Power storage unit 1280 Power control unit 1282 Steering unit 1284 Propulsion drive unit 1286 Position detection unit 1288 Date / time data storage unit 1290 Wireless communication unit 1291 Various sensors 1292 Main control unit

JP 2002-2111496 A

Claims (10)

A flying object,
The main body,
A propulsion unit that propels the main body in the direction of travel;
A solar cell film which is a film-like solar cell;
A storage unit for storing the solar cell film in a state in which one end thereof is connected;
The main body is
A storage drive unit that drives the storage unit and expands the solar cell film from the storage unit to the rear in the traveling direction in a state where the one end of the solar cell film is connected to the storage unit;
A power storage unit that stores electric power generated by the solar cell film;
A propulsion drive unit that drives the propulsion unit using power generated by the solar cell film or power stored in the power storage unit; and
A flying object characterized by comprising: The main body is
A steering part for controlling the traveling direction of the main body part;
A position detector for detecting the position of the main body,
2. The flying object according to claim 1, wherein the storage drive unit drives the storage unit to deploy the solar cell film when the detected position reaches a predetermined altitude of the stratosphere. .   The storage drive unit drives the storage unit to store the deployed solar cell film in the storage unit when the detected position deviates from a predetermined altitude of the stratosphere. The flying object according to claim 2. A flying system comprising a first flying object and a second flying object, which are the flying objects according to claim 1,
The second projectile is
A second main body connected to the other end of the solar cell film;
A second propulsion part for propelling the second main body part in the traveling direction,
The second body part is
A second power storage unit that stores power generated by the solar cell film;
And a second propulsion drive unit that drives the second propulsion unit using electric power generated by the solar cell film or electric power stored in the second power storage unit.   When the storage unit is driven, the second propulsion drive unit temporarily reduces the driving force of the second propulsion unit to lower the speed of the second flying object than the speed of the first flying object. The flight system according to claim 4, wherein the solar cell film is deployed backward in the traveling direction from the storage unit.   When the solar cell film is deployed, the second main body portion controls the traveling direction of the second main body portion so that the altitude of the second flying body is lower than the altitude of the first flying body. The flight system according to claim 4, further comprising a second steering unit that performs the operation. The second body part is
A position detector for detecting the position of the second main body,
A date / time data storage unit for storing date / time data;
The second steering unit controls the altitude of the second flying object according to the position of the second main body unit and the absolute solar position based on the date and time data when the solar cell film is deployed. The flight system according to claim 6, wherein The main body is
A light detection unit for detecting the position of the sun;
The steering unit controls the inclination of the main body so that the main body is positioned perpendicular to the detected position of the sun. The flight system described. The main body is
A calculation unit for calculating wind conditions;
When the wind condition satisfies a predetermined condition, a notification unit for notifying that effect,
The flight system according to any one of claims 4 to 8, further comprising: A flying method of a flying object,
The flying object is
The main body,
A propulsion unit that propels the main body in the direction of travel;
A solar cell film which is a film-like solar cell;
A storage unit for storing the solar cell film in a state in which one end thereof is connected;
A storage drive unit drives the storage unit to expand the solar cell film from the storage unit to the rear in the traveling direction in a state where the one end of the solar cell film is connected to the storage unit. Steps,
An electricity storage step in which the electricity storage unit stores the electric power generated by the solar cell film,
A propulsion drive unit that drives the propulsion unit using the electric power generated by the solar cell film or the electric power stored in the electric storage step; and
A flight method comprising:

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