Side thruster system and flying object

Abstract

To provide a side thruster system with a higher degree of freedom in orientation control.SOLUTION: According to an embodiment, a side thruster system mounted on a flying object comprises a plurality of first side thrusters and a plurality of second side thrusters. The plurality of first side thrusters are provided along a first circumference where a plane perpendicular to an axis of the flying object intersects with an outer shell of the flying object. The plurality of second side thrusters are provided along a second circumference that is parallel to the first circumference along the axis.SELECTED DRAWING: Figure 2

Description

[Technical Field]

[0001] FIELD An embodiment of the present invention relates to a side thruster system and a flying vehicle. [Background technology]

[0002] Aerodynamic steering is a steering technology that changes the position and controls the attitude of a flying object. Aerodynamic steering utilizes the aerodynamic forces generated by movable wings. Side thrusters, known as one type of steering technology, generate force using gas ejected from burning solid fuel. This allows for a faster response than aerodynamic steering. [Prior art documents] [Patent documents]

[0003] [Patent Document 1] Japanese Patent Application Laid-Open No. 2013-178062 [Patent Document 2] Japanese Patent Application Laid-Open No. 2003-240500 [Patent Document 3] Japanese Patent Application Laid-Open No. 2003-294398 [Patent Document 4] Patent No. 4305796 Summary of the Invention [Problem to be solved by the invention]

[0004] Among the types of side thrusters, the impact diverted type is a type that obtains thrust in the lateral direction by ejecting gas from the outer shell of the projectile. In the impact diverted type, thrust is obtained by burning solid fuel to generate ejected gas.

[0005] However, once solid fuel is ignited, it continues to burn until the fuel is used up, making it impossible to control its attitude during that time. Vehicles equipped with existing impact-diverted side thrusters have had the disadvantages of being unable to correct their attitude in any direction other than the direction of the ejected gas, or being able to control it only in one direction.

[0006] An object is to provide a side thruster system with enhanced degrees of freedom in attitude control and a flying object.

Means for Solving the Problems

[0007] According to an embodiment, a side thruster system mounted on a flying object includes a plurality of first side thrusters and a plurality of second side thrusters. The plurality of first side thrusters are installed along a first circumference where a plane perpendicular to the axis of the flying object intersects the outer shell of the flying object. The plurality of second side thrusters are installed along a second circumference parallel to the first circumference along the axis.

Brief Description of the Drawings

[0008]

Figure 1

Figure 2

Figure 3

Figure 4

Figure 5

Figure 6

Modes for Carrying Out the Invention

[0009] FIG. 1 is a block diagram showing an example of a flying object according to an embodiment. The flying object 1 includes a guidance device 3, a propulsion device 5, and a steering device 6. The guidance device 3 detects a target 2 and outputs a steering signal for guiding the flying object 1 to the target 2 to the steering device 6. The propulsion device 5 is a propulsion mechanism for flying the flying object 1. The steering device 6 as a steering mechanism controls the flight of the flying object 1 based on the steering signal given from the guidance device 3 and guides the flying object 1 to the target 2.

[0010] The guidance device 3 includes an antenna unit 7, a processor 8, a sensor unit 9, and a side thruster system 10. The antenna unit 7 is, for example, a phased array antenna including a plurality of antenna elements. The antenna unit 7 radiates an irradiation radio wave 21 to the target 2 while scanning a transmission beam. Also, the antenna unit 7 receives a reflected radio wave 22 from the target 2 while scanning a reception beam. Further, the antenna unit 7 frequency-converts the received radio wave to enable signal processing and outputs it to the processor 8.

[0011] The sensor unit 9 acquires various sensor data related to the flight of the flying object 1. The sensor data may include, for example, at least any one of the speed of the flying object 1, the position of the flying object 1, and the acceleration of the flying object. These sensor data can be acquired, for example, using an inertial navigation device or a satellite positioning system.

[0012] The side thruster system 10 includes a plurality of impact driver type side thrusters. FIG. 2 is a diagram showing an example of the equipment of a side thruster according to an embodiment. The side thruster system includes a plurality of side thrusters equipped along the circumferential direction of the outer shell of the flying object 1. Let the side thrusters be side thrusters 11a, 11b, and 11c in order from the side closer to the tip of the flying object 1. That is, the side thrusters are equipped along a circumference where a plane perpendicular to the axis of the flying object 1 intersects the outer shell of the flying object 1.

[0013] The plurality of side thrusters 11a each generate the same thrust. Similarly, the side thrusters 11b and 11c each generate the same thrust. On the other hand, in the embodiment, it is assumed that the thrusts generated by the side thrusters 11a, 11b, and 11c are different from each other. For example, (thrust of side thruster 11a > thrust of side thruster 11b > thrust of side thruster 11c).

[0014] Returning to FIG. 1 again to continue the explanation. The processor 8 performs processes such as generating and controlling the waveform of the irradiation radio wave 21, detecting the target 2 included in the reflected radio wave 22, or analyzing the sensor data acquired by the sensor unit 9. Based on these processes, the processor 8 generates a control signal for guiding the flying object 1 toward the target 2 and outputs it to the propulsion device 5, the steering device 6, and the side thruster system 10. The side thrusters 11a, 11b, and 11c are individually controlled by the processor 8 for the ignition timing and the like. That is, the processor 8 controls the side thruster system 10 based on the sensor data acquired by the sensor unit 9.

[0015] FIG. 3 is a diagram showing an example of the solid fuel of the side thruster. In the circumferential direction, solid fuels of the same size are used. In the axial direction of the machine axis, solid fuels of different sizes are used. The combustion time of the side thruster is approximately proportional to the amount of fuel. In the embodiment, (combustion time of side thruster 11a > combustion time of side thruster 11b > combustion time of side thruster 11c).

[0016] As it approaches the tip of the flying object 1, it moves away from the center of gravity of the flying object 1, so the moment of force increases. Therefore, in the order of the side thrusters 11a, 11b, and 11c, the force for changing the flight direction of the flying object 1 increases.

[0017] FIG. 4 is a diagram for explaining the effect when the side thruster in the axial direction of the machine axis is operated. By changing the operation timing of the side thrusters (for example, 11a and 11c) installed at different positions in the axial direction of the machine axis, it becomes possible to correct the pitch angle of the flying object 1 during flight.

[0018] FIG. 5 is a diagram for explaining the effects when the circumferential side thrusters are operated. FIG. 5 shows a state in which the flying object is sliced when viewed from the front in the propulsion direction. The side thrusters mounted in the circumferential direction generate the same thrust respectively. By operating a plurality of side thrusters mounted in the circumferential direction, thrust can be generated not only in the mounting direction of the side thrusters but also in the direction between the side thrusters, and the position can be changed.

[0019] For example, when the side thrusters adjacent to each other in the circumferential direction are ignited simultaneously, the thrust indicated by the solid line is generated in each side thruster, and the thrust of the dotted line is obtained as the resultant force. The flying object 1 will change its position in the direction opposite to the resultant force (the dashed-dotted line).

[0020] FIG. 6 is a diagram for explaining the effects when the side thrusters in the axial direction and the circumferential direction are operated. By combining the side thrusters in the axial direction and the circumferential direction, for example, by operating the side thrusters 11a and 11c with different positions in the axial direction, a complex rotational moment including, for example, the roll direction and the pitch direction (yaw direction) can be generated simultaneously. Thereby, not only the position change but also the attitude control including the pitch angle and the like can be performed simultaneously.

[0021] As described above, in the embodiment, a plurality of impact diver type side thrusters are mounted in the axial direction and the circumferential direction of the flying object to form a side thruster system. The magnitudes of the thrusts generated by the side thrusters mounted in the same circumferential direction are made equal, and the magnitudes of the thrusts and the combustion times of the side thrusters mounted on different circumferences are made different. In this way, by arranging side thrusters with equal thrust magnitudes in the circumferential direction and side thrusters with different generated thrust magnitudes in the body axis direction, fine attitude control of the flying object becomes possible. From these, according to the embodiment, it is possible to provide a side thruster system and a flying object with increased degrees of freedom in attitude control.

[0022] Note that the present invention is not limited to the above-described embodiments. For example, although an example of providing three types of side thrusters 11a, 11b, and 11c has been shown, at least two types of side thrusters (for example, 11a and 11b) having different thrusts or combustion times may be provided. Alternatively, four or more types of side thrusters may be provided.

[0023] Although the embodiments have been described, these embodiments are presented as examples and are not intended to limit the scope of the invention. This novel embodiment can be implemented in various other forms, and various omissions, replacements, and changes can be made without departing from the gist of the invention. This embodiment and its modifications are included in the scope and gist of the invention, and are also included in the invention described in the claims and its equivalent scope.

Explanation of Reference Numerals

[0024] 1... flying object, 2... target, 3... guidance device, 5... propulsion device, 6... steering device, 7... antenna unit, 8... processor, 9... sensor unit, 10... side thruster system, 11a... side thruster, 11b... side thruster, 11c... side thruster, 21... transmitted radio wave, 22... reflected radio wave.

Claims

1. A side thruster system mounted on a flying object, comprising: a plurality of first side thrusters installed along a first circumference where a plane perpendicular to the axis of the flying object intersects the outer shell of the flying object; a plurality of second side thrusters installed along a second circumference parallel to the first circumference along the axis of the flying object.

2. The thrust of each of the first side thrusters is equal, The thrust of each of the second side thrusters is equal. The side thruster system according to Claim 1.

3. The thrust of the first side thrusters is greater than that of the second side thrusters. The side thruster system according to Claim 2.

4. The combustion time of the first side thrusters is longer than that of the second side thrusters. The side thruster system according to Claim 1.

5. The first circumference is closer to the tip of the flying object than the second circumference. The side thruster system according to Claim 1.

6. The first side thrusters and the second side thrusters are of the impact deflector type. The side thruster system according to Claim 1.

7. A side thruster system according to any one of Claims 1 to 6, a sensor unit for acquiring sensor data, a flying object comprising a processor for individually controlling the plurality of first side thrusters and the plurality of second side thrusters based on the sensor data.

8. The sensor data includes at least one of the speed of the flying object, the position of the flying object, and the acceleration of the flying object. The flying object according to Claim 7.

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