JP2003114096A - Flying object - Google Patents

Abstract

(57) [Summary] [Problem] To extend the range of a flying object, and to deal with a target object that has been addressed by launching a flying object from an aircraft, using a flying object launched from the ground. SOLUTION: A plurality of guided flying objects are arranged around a base unit rocket, and immediately after the base unit rocket is launched, the propulsion device of the base unit rocket is used to fly around. After the base unit rocket enters a target range, it is set around. By launching the guided flying vehicle and guiding the guided flying vehicle after launch with the base rocket, a guided flying vehicle with a long range can be obtained.

Description

Detailed Description of the Invention

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a flying body which is launched toward a target body such as an aircraft or a guided missile and flies toward the target body.

[0002]

2. Description of the Related Art Conventionally, after being launched toward a target object such as an aircraft or a guided missile, it is separated into a plurality of guide projectiles during flight toward the target object, and the guide projectile after separation. Was proposed a compound guidance flying body that flies toward a target body. This type of complex guided vehicle has the character of a ground-to-air guided vehicle because it is launched from the ground, and because the guided vehicle separates in the air and associates with the target object, air-to-air guided vehicle Also has a character as a flying object. Therefore, regarding the conventional guided vehicle, the features of the ground-to-air guided vehicle and the air-to-air guided vehicle will be described below.

FIG. 6 shows a flow of operation of a conventional ground-to-air guided vehicle. In FIG. 6, 1 is a launching device, 2 is an aerial device that issues a guidance command, 3 is a conventional ground-to-air guiding vehicle, and 4 is a target object. The ground-to-air guided flying object 3 launched from the launching device 1 flies toward the target object while receiving the guidance command from the antenna device 2. After approaching the target object by a certain distance, the guidance device mounted on the ground-to-air guidance vehicle starts autonomous guidance. After capturing the target object, the target object is tracked as it is, and finally the target object is associated.

FIG. 7 shows a flow of operation of a conventional air-to-air guided vehicle. In FIG. 7, 5 is a conventional air-to-air guided aircraft, 6 is a mother aircraft of the guided aircraft, and 4 is a target object. Further, the distance R2 from the target body represents the distance at which the guided flying body 5 can be launched to the target body 4, and the distance R1 enables the active radio wave sensor of the guided flying body 5 to be effectively used. Indicates the distance. The mother aircraft 6 launches the guided flying vehicle 5 near the distance R2. And
Until the guided flying object 5 approaches the target object 4 within a fixed distance R1, the mother machine 6 irradiates the target object 4 with radar and transmits the position of the target object 4 to the guided flying object 5. In this way, the guided flying object 5 is guided. When the distance from the target body 4 is less than R1, the guided flying body 5 starts autonomous guidance and associates with the target body 4.

[0005]

In the conventional propulsion device for a guided flying vehicle as described above, the propellant is usually burned in a short time after being launched from the ground in a single stage, and then inertial flight is performed. The propulsive performance of such a guided vehicle will be described with reference to FIG. In FIG. 8, reference numeral 7 represents a conventional guide vehicle, and 8 represents a propulsion device thereof. Fig. 8 (a) shows the moment when the combustion of the propelling device for the flying vehicle starts, where v is the velocity of the aircraft, v _{0 is} the initial velocity of the aircraft, and uu is the discharge velocity of the combustion gas (relative velocity to the flying vehicle) There is. Assuming that external forces such as air resistance do not act on the guided vehicle, let the acceleration rate of the guided vehicle (speed increment obtained after using all fuel) be v _f , let the effective exhaust velocity be u, and guided flight _Let μ _f be the ratio of the final mass m _{f of the} body to the initial mass m ₀ . The effective exhaust velocity represents an exhaust gas velocity equivalent to the sum of momentum thrust and pressure thrust, and is one of the indexes indicating the performance of a propulsion device. FIG. 8B shows the state at the end of combustion, where the speed of the machine is (v ₀ + v _f ). At this time, the acceleration rate v _f
Can be expressed as

[0006]

[Equation 1]

Generally, it is considered that the larger the acceleration velocity v _f is, the larger the range of the guided vehicle is. Therefore, it is desirable that this value is large. According to Equation 1, the acceleration rate v _f can be increased by reducing the mass ratio μ _f as much as possible. However, the mass ratio μ _f limits the size of the guided vehicle,
It is determined by the capacity of the mounted equipment and the type of propellant, and the effective exhaust velocity u is almost determined by the type of propellant. Therefore,
As long as the propulsion device has a single stage, it is not possible to expect an increase in the acceleration velocity v _f , that is, a large extension of the range of the guide vehicle.

On the other hand, in the case of the ground-to-air guided vehicle, it is very expensive to fly the propulsion device for each guided vehicle in order to extend the range. It is not a good idea.

When an air-to-air guided vehicle is used for a target object, the mother aircraft on which the guided vehicle is mounted has a distance R shown in FIG.
You must carry the guided flight until you approach the target up to 1. Therefore, there is a possibility that the mother aircraft may fall within the range of other flying objects mounted on the target object.

The present invention has been made to solve the above-mentioned problems, and aims to extend the range of a guided flying object so that it can fly toward a target object without being transported to the vicinity of the target object by an aircraft. The purpose is to obtain a guided flying vehicle.

[0011]

According to a first aspect of the present invention, there is provided a guided vehicle including a mother rocket provided with a first steering blade and a first propulsion device, and a body provided with a second steering blade. A radio wave sensor for detecting a target, a guide device for guiding the machine body to the target based on the detection information of the radio wave sensor, and a second propulsion device for giving propulsive force to the machine body, and the mother rocket at the time of launching The guidance vehicle from the mother rocket according to the position of the guidance flying body on which the second propulsion device operates after being separated from the mother rocket and the target body after launch and the flight state of the aircraft. It is provided with a separation mechanism for separating a flying body, and a data link device for communicating between the guiding flying body and the mother rocket after the separation of the guided flying body by the separating mechanism.

According to the second aspect of the invention,
The first body with the steering wing, the first to detect the target
Radio sensor, a first guiding device for guiding the first machine body to a target based on detection information from the first radio sensor,
And a mother rocket having a first propulsion device that applies a propulsive force to the first body, a second body provided with a second steering blade, a second radio wave sensor for detecting a target, the second A second guiding device that guides the second body to a target based on the detection information of the second radio wave sensor, and a second propulsion device that applies a propulsive force to the second body. The mother machine is mounted on a mother machine rocket, and the plurality of guided flying bodies that operate the second propulsion device after separation from the mother machine rocket, the positions of the target body after launch, and the flight state of the mother machine are used. A separation mechanism for separating each of the guided vehicles from a rocket, and a data link device for performing communication between each of the guided vehicles and the mother rocket after separating the guided vehicle by the separation mechanism With That.

In the guided vehicle according to the third aspect of the invention, the mother rocket is composed of a multi-stage separation rocket that is separated in multiple stages.

In the guided vehicle according to the fourth aspect of the present invention, the mother rocket transmits a separation command and an ignition command to the guided vehicle before the separation in accordance with the positions of a plurality of targets and the flight state of the mother rocket. In addition, the data link device is provided with a flight control unit that generates a command to set a target object on the guide vehicle after the separation, and the data link device guides the command from the mother rocket to the guide vehicle after the separation. Is to be transmitted to.

In the guided aircraft according to the fifth aspect of the invention, each of the guided aircraft is provided with a data link device for mutual communication.

[0016]

BEST MODE FOR CARRYING OUT THE INVENTION Embodiment 1. Embodiment 1 according to the present invention will be described with reference to FIGS. 1 and 2. FIG. 1 is a diagram showing a structure of a composite guided vehicle in this embodiment, FIG. 1 (a) is a side view of the composite flying object, and FIG. 1 (b) is a view of the composite flying object. It is a figure when a shovel is seen from the nose to the direction of the tail. In the figure, reference numeral 9 denotes a mother rocket, and 10 denotes a guided vehicle. In the first embodiment, as an example, four guided vehicles 10 are arranged around the mother rocket 9. The number of the guided aircraft 10 arranged around the mother rocket 9 may be any number corresponding to the propulsive force of the mother rocket, and is not necessarily four. The guided vehicle 10 includes a guiding device 11, a gyro 12, a data link receiving device 13 for a mother rocket, a control unit 14, and a propulsion device 15. The mother machine rocket 9 is provided with a compound guide vehicle guidance device 16, a flight control unit 17, a first stage propulsion device 18, a second stage propulsion device 19, steering wings 20, a guide vehicle suspension and separation mechanism 21. In this example, the propulsion device of the mother rocket 9 has two stages, but it does not necessarily have to have two stages.

Next, the operation will be described. FIG. 2 is a schematic diagram showing the flight procedure of the composite guided vehicle of the present invention. In FIG. 2, 22 is a launching device for launching the mother rocket 9 from the ground, 23 is the first stage of the mother rocket, and 24
Shows the second stage rocket of the mother rocket. The definition of the term relating to the stage of the rocket is shown in FIG. 5, in which 27 is the first stage and 28 is the second stage which is stacked above the first stage.
Tier, 29 is the third tier stacked on top of the second tier, 30 is the first
A first stage rocket consisting of stage 27, second stage 28 and third stage 29, 31 is a second stage rocket comprising second stage 28 and third stage 29, 32 is a third stage rocket comprising third stage For convenience of explanation, the numbers in this figure are different from those in other figures such as FIGS. 1 and 2.

The composite guided vehicle launched from the launch device 22 on the ground is the propulsion device 1 of the first stage 23 of the mother rocket.
Use 8 to fly a certain distance. Thereafter, radar irradiation is performed by the guidance device 16 of the mother rocket 9, and the target body 4 is captured. At this time, the guiding device 16 measures the existing direction of the target and the distance to the target based on the reflected wave that is emitted from the radar toward the target and reflected from the target. As a result of this distance measurement, when it is detected that the target object 4 is within the range of the guide vehicle 10, the flight control unit 17 issues a command for separating the guide vehicle 10 and an ignition command for the propulsion device. Then, all the guided vehicles 10 are simultaneously separated by the guided vehicle suspension and separation mechanism 21, and the propulsion device 15 is ignited. In the mother rocket 9, the mother rocket first stage 23 is then separated and
The stage propulsion device 19 is ignited. The mother aircraft second stage rocket 24 tracks the target object 4 and transmits a guidance command to the guidance vehicle 10 via a data link. Guided flight 10
When it becomes possible to capture the target body 4 by the guidance device 11 of its own machine, the robot shifts to autonomous guidance and associates with the target body 4.
The mother rocket first stage 23 and the mother machine second stage rocket 24 were described as being separated within the target range. However, this separation was not performed according to the flight distance required to guide the target. The mother rocket may be a single stage, and only the mother rocket and a plurality of guided vehicles may be separated.

Embodiment 2. A second embodiment according to the present invention will be described with reference to FIGS. 3 and 4. FIG. 3 is a diagram showing the structure of the composite guided vehicle in this embodiment. The difference from FIG. 1 is that the propulsion device of the mother rocket is a single stage (only 26 in FIG. 3), and the receiving device 13 is replaced with a data link device 25 between the guide vehicles 10. That's it. Embodiment 2
In this example, four guided aircraft 10 are arranged around the mother rocket 9 as an example.
The number of 0 may be any number commensurate with the propulsive force of the mother rocket, and is not necessarily four. Although FIG. 3 illustrates a case where the propulsion device for the mother rocket has a single stage, the propulsion device for the mother rocket may have multiple stages.

Next, the operation will be described. In this form, the mother rocket does not participate in guiding the guided vehicle. FIG. 4 is a schematic diagram showing the flight procedure of the composite guided vehicle of the present invention. The composite flying body launched from the launch platform 22 on the ground is the mother rocket propulsion device 26.
To fly a certain distance. The guidance during this period is performed by the guidance device 16. After that, after the target object enters the range of the guided flight object 10, the flight control unit 1
7 issues a command to separate the guide vehicle 10 and a command to ignite the propulsion device, and all the guide projectiles 10 are simultaneously separated by the guide vehicle suspension separation mechanism 21 and the propulsion device 15 is ignited. The guide vehicle 10 grasps the positions of a plurality of target bodies by the guide device 11 of the active radio wave sensor system, and the data link device 25 between the guide vehicles.
While exchanging information with each other, each guidance aircraft is adjusted to set a different target object as much as possible.
After the target of each guided flight object is determined, guidance is performed by the guidance device of each guided flight object until the target object 4 is met.

In the first and second embodiments described above, the propulsion device can be regarded as a multi-stage structure as a whole. Even if the propulsion device of the mother rocket is a single stage, the propulsion device of the guided vehicle is ignited after being propelled to some extent by the propulsion device of the mother rocket, and as a result, the propulsion device has a multi-stage configuration. When the propulsion device has a multi-stage structure, it is possible to obtain the effect of extending the range as a flying object. Here, the principle that the range is extended when the propulsion device has a multi-stage configuration will be briefly described.

FIG. 5 shows a three-stage rocket. Although the number of stages is three in FIG. 5, the following discussion considers the number of stages as N. Where M _i is the initial mass of the i-th stage rocket, m
_pi is the propellant mass of the i-th stage, u _i is the effective pumping speed of the i-th stage rocket. Stage i rocket (i = 1,2, ..., N)
Refers to the whole above, including the i-th stage itself. The idea of this i-stage rocket is that when calculating the acceleration, it is considered as one rocket including all stages above the burning stage, and the acceleration is calculated from the mass ratio of the rocket before and after combustion. You will need it. The mass ratio of the i-th stage rocket is defined as

[0023]

[Equation 2]

Based on the above definition, the initial velocity is zero and the acceleration velocity v _i by the i-th stage rocket and the final velocity v _fN of the N-stage rocket are as shown in equations 3 and 4, respectively.

[0025]

[Equation 3]

[0026]

[Equation 4]

According to Equation 4, the speed increase rate is determined only by the effective exhaust speed and the mass ratio. Since the effective exhaust velocity is almost determined by the fuel, the mass ratio may be reduced to increase the acceleration rate. When the effective pumping speeds of the propulsion engines of all stages are all equal, the final velocity of the Nth stage rocket can be expressed as shown in Formula 5.

[0028]

[Equation 5]

According to Equation 5, since the product of the mass ratios of the respective stage rockets becomes the overall apparent mass ratio, the apparent mass ratio can be made small even if the mass ratio of the respective stage rockets is not so small. . Therefore, it is easier to increase the acceleration rate when the propulsion device has multiple stages than when it has a single stage, and as a result, it is easy to increase the range.

[0030]

Since the flying object according to the present invention is constructed as described above, it has the following effects.

According to the present invention, since the propulsion device has a multi-stage structure as a whole, a range stretching effect can be obtained. Also, since the guided aircraft is launched from the mother rocket,
The launching aircraft will not be within range of the target to launch the projectile, as would be the case when launching from an aircraft.

Further, according to the present invention, since the guided flying object can be separated at a position close to the target object, it is deceptive as if the guided flying object is one until it approaches the position closer to the target object. You can Therefore, it becomes difficult for the target object to take an appropriate avoidance action, and the accuracy of the guided flying object is improved.

[Brief description of drawings]

FIG. 1 is a schematic diagram showing a first embodiment of a composite guided vehicle of the present invention.

FIG. 2 is a schematic diagram showing a flight procedure of the first embodiment of the composite guided vehicle of the present invention.

FIG. 3 is a schematic diagram showing Embodiment 2 of the composite guided vehicle of the present invention.

FIG. 4 is a schematic diagram showing a flight procedure of a second embodiment of the composite guided vehicle of the present invention.

FIG. 5 is a diagram showing a configuration of a multistage rocket.

FIG. 6 is a diagram showing a flow of operation of a conventional ground-to-air guided vehicle.

FIG. 7 is a diagram showing a flow of operation of a conventional air-to-air guided vehicle.

FIG. 8 is a diagram illustrating a conventional propulsion device for a flying vehicle.

[Explanation of symbols]

1 launcher 2 Antenna device 3 Conventional surface-to-air guided air vehicle 4 target body 5 Conventional air-to-air guided air vehicle 6 mother plane 7 Conventional guidance aircraft 8 propulsion devices 9 mother rocket 10 guided flight 11 induction device 12 Gyro 13 Receiver 14 Control unit 15 Propulsion device 16 Compound guidance aircraft guidance device 17 Flight Control Department 18 1st stage propulsion device 19 Second stage propulsion system 20 steering wings 21 Guided Aircraft Suspension and Separation Mechanism 22 launcher 23 Mother Rocket First Stage 24 mother aircraft second stage rocket 25 Data Link Device 26 Propulsion device 27 First Stage 28 Second stage 29 Third Stage 30 First Stage Rocket 31 Second Stage Rocket 32 Third Stage Rocket

Claims (5)

[Claims] 1. A mother rocket provided with a first steering wing and a first propulsion device, a body provided with a second steering wing, a radio wave sensor for detecting a target, and detection information of the radio wave sensor. A guidance device for guiding the aircraft to a target based on
And a second propulsion device that gives propulsive force to the aircraft, is mounted on the mother rocket at the time of launch, and is a guide flying body that operates the second propulsion device after separation from the mother rocket, and launch Depending on the position with the target object afterwards and the flight state of the aircraft, a separation mechanism that separates the guide vehicle from the mother rocket, and the guide flight after the guide vehicle is separated by the separation mechanism A flying body comprising a data link device for communicating between the body and the mother rocket. 2. A first airframe provided with a first steering blade,
A first radio wave sensor for detecting a target, a first guiding device for guiding the first airframe to the target based on detection information of the first radio wave sensor, and a first force applying propulsive force to the first airframe. The mother rocket having the first propulsion device, the second body provided with the second steering blade, the second radio wave sensor for detecting the target, and the second radio wave sensor based on the detection information of the second radio wave sensor. And a second propulsion device that guides the second body to a target, and a second propulsion device that applies a propulsive force to the second body, is mounted on the mother rocket at the time of launch, and is separated from the mother rocket. The guide vehicles are separated from the mother rocket in accordance with the positions of the plurality of guided vehicles after which the second propulsion device operates and the target body after launch and the flight state of the aircraft. Separation mechanism and the separation mechanism After separation of the conductive flying object, flying body and a data link device which performs communication with the base unit rockets and said respective inductive spacecraft. 3. The flying vehicle according to claim 1, wherein the mother rocket is composed of a multistage separation rocket that is separated into multiple stages. 4. The mother rocket transmits a separation command and an ignition command to the guidance vehicle before the separation according to the positions of a plurality of target bodies and the flight state of the mother rocket, and the guidance flight after the separation. A flight control unit for generating a command to set a target object on a vehicle, wherein the data link device transmits the guidance command from the mother rocket to the guidance vehicle after the separation. The flying vehicle according to item 1 or 2. 5. The flying vehicle according to claim 2, wherein each of the guided flying vehicles includes a data link device for mutual communication.