JP2013178062A - Vertical launch missile and launch device thereof - Google Patents

Abstract

PROBLEM TO BE SOLVED: To provide a vertical launch missile that flies easily towards a target at an early stage to a direction close to substantially horizontally with a gyration radius being small, and to provide a launch device thereof.SOLUTION: A vertical launch missile 10 has: a body part 11; a head part 12 provided in front of the body part 11; a rear part 13 provided behind the body part 11; a rocket motor 17 provided in this rear part 13 for generating thrust; a side thruster 15 provided in the body part 11 for jetting gas; and a gas generation part 16 for supplying this side thruster 15 with the gas, and is launched vertically above by the launch device, wherein the missile 10 is launched by a launch mechanism provided in the launch device when launched.

Description

  Embodiments of the present invention relate to a vertical launch vehicle and its launch device that can be fired substantially vertically and thereafter change attitude.

  When the flying object makes a turn to change the traveling direction, aerodynamic steering is usually used. Therefore, in order to turn, it is necessary to fly at a considerable speed. In other words, since the magnitude of acceleration required for turning depends on the speed of the missile, in the case of a flying object that launches vertically, if it is waiting for the speed to increase, it will only fly up. It is difficult to change the course in the direction of the direction until the altitude rises.

  In order to cope with this problem, many of the conventional vertical launching vehicles have a mechanism (TVC (Thrust Vector Control) mechanism; side thruster) that directly changes the direction of thrust, and even turn at low speed. It has a function that can.

  When performing a turn to change the direction by the side thruster, it is possible to make a turn with a smaller radius compared to aerodynamic steering, and to fly in a desired horizontal direction at a low altitude.

  However, since the rocket motor that propels the flying object is normally ignited in the conventional flying object, the speed after ignition increases, and this increase in speed during turning makes the turning radius larger. The enlargement of the turning radius means a delay in the arrival time to the target point, which in turn causes a reduction in the hit performance. That is, the flying object whose speed has been increased by the rocket motor makes a large turn and takes a long time to reach the target, and it becomes difficult for the flying object to accurately reach the target.

  In addition, the fuel for the power of the rocket motor is also necessary, which contributes to the heavy turning of the flying object.

  In addition, a flying body that includes a gas generator in the flying body itself and uses the generated gas as a propulsive force and also serves as a jet flow of a side thruster is known.

JP-A-6-331300

  The present invention provides a vertical launch vehicle and its launching device that have a small turning radius and are easy to fly toward a target in a direction that is almost horizontal at an early stage.

  In order to solve the above problems, an embodiment includes a trunk portion, a head portion provided in front of the trunk portion, a rear portion provided after the trunk portion, and a rear portion provided in the rear portion, and a propulsive force. A flying body that has a rocket motor that generates gas, a side thruster that is provided in the body section and injects gas, and a gas generation section that supplies gas to the side thruster, and is launched vertically by a launcher. The vertical launching vehicle is characterized in that when it is launched, it is launched by a launching mechanism provided in the launching device.

It is a lineblock diagram of the vertical launching flying object concerning one embodiment. It is a figure which shows the structural example of the flying body control part in FIG. It is a figure which shows the structural example of the flying body launcher of one Embodiment. It is a figure which shows the structural example of the side thruster of the vertical launching flight body of FIG. It is a figure for demonstrating operation | movement of the flying body and launching apparatus of one Embodiment. It is a figure for demonstrating the modification of embodiment.

  Hereinafter, embodiments of the present invention will be described with reference to the drawings. A simple configuration of the flying object of the embodiment is shown in FIG.

  A vertical launching flying object (hereinafter abbreviated as flying object) 10 includes a trunk portion 11, a head portion 12 provided in front of the trunk portion 11, and a rear portion 13 provided behind the trunk portion 11. And a pair of front wings 14 a provided forward on the side surface of the body portion 11, and a pair of rear wings 14 b provided rearward on the side surface of the body portion 11.

  In front of the front wing 14a of the body 11, a side thruster 15 capable of injecting gas to the outside substantially perpendicular to the peripheral surface is provided, and the gas generated by the gas generation control unit 16 is supplied. Is done.

  The rear part 13 of the flying body 10 is provided with a rocket motor 17 that generates a forward thrust when the flying body 10 is flying. The gas generation control unit 16 and the rocket motor 17 are controlled by the flying object control unit 18.

  A configuration example of the flying object control unit 18 is shown in FIG. The flying object control unit 18 sends a control signal to the side thruster so that the target detection unit 21 that detects the target, the motor drive control unit 22 that controls the drive of the rocket motor 17, and the gas generation unit 16. The generation control unit 23, the time measurement unit 24 that measures the time after the flying object 10 is launched, the speed detection control unit 25 that detects and controls the speed of the flying object 10, and the flying object 10 It has an attitude detection unit 26 that detects the attitude, and a main control unit 27 that controls these units.

  FIG. 3 shows a state where the flying object 10 is accommodated in the launching device. The flying object launching device 31 is a cylindrical support 32 that houses the flying object 10 and supports it in the vertical direction at the time of launching, and a launching mechanism that is provided at the bottom of the support 32 and pushes the flying object vertically upward. 33.

  The launching mechanism 33 places and fixes the flying body 10 at the time of launching, a placing part 34 that also serves as a piston that can move in the vertical direction, and a gas generator 35 that generates high-pressure gas that pushes up the placing part 34 from below. The gas generator 35 has an igniter 36 that ignites the gas. The gas generator 35 is ignited by the igniter 36 and the mounting portion 34 is rapidly raised upward, thereby launching the flying object placed on the mounting portion 34.

  Details of the configuration example of the side thruster shown in FIG. 1 are shown in FIGS. FIG. 4A is a longitudinal sectional view of the flying object, and FIG. 4B is a vertical sectional view thereof.

  As shown in FIG. 4 (b), four nozzles 15a, 15b, 15c, 15d are provided around the body 11 of the flying body 10, and gas compartments 16a, 16b, 16c, 16d are connected to the nozzles. ing. These gas compartments are connected to the gas generator 16. The side thruster has these nozzles and gas compartments.

  Next, the operation in which the flying object 10 is launched from the flying object launching device 31 will be described based on the flowchart shown in FIG.

  When an instruction for launching the flying object 10 is received in step S401, the operation of the launch mechanism 33 is started in step S402. That is, gas is generated by the gas generator 35 and the flying object 10 placed on the placement unit 33 is fired vertically upward.

  In step S404, time measurement is started in the time measurement unit 24 of the flying object control unit 18 shown in FIG. On the other hand, the speed detection control unit 25 detects the speed of the flying object 10. In step S405, the target detection unit 21 detects the target altitude. In the next step S406, the altitude of the flying object is calculated from the product of the speed detected by the speed detection control unit 25 and the time measured by the time measurement unit 24.

  In step S407, it is determined whether or not the flying object 10 has reached the same altitude as the target. In this determination, the main control unit 27 compares the product of the target altitude obtained by the target detection unit 21 with the time obtained by the time measurement unit 24 and the speed obtained by the speed detection control unit 25, that is, the calculated altitude. Is done.

  When it is detected in step S407 that the flying object 10 has reached the target altitude, the target detection unit 21 detects the target direction. Then, a gas for the side thruster is generated in the gas generation unit 16. With respect to the target direction detected in step S407, the gas generated in the gas generator 16 is supplied to the side thruster 15 on the opposite side, and injected outside (step S410).

  For example, if the target is detected in the direction of the nozzle 15b shown in FIG. 4B, the gas is sent from the gas generation unit 16 to the gas compartment 16a, and the gas is injected from the nozzle 15a. In this way, the flying object 10 can be turned in the direction of the nozzle 15b.

  In this way, the flying object 10 is directed in the target direction, and in step S411, the flying object 10 is directed in the target direction. The postures of these flying bodies 10 are sequentially grasped by the posture detection unit 26.

  In addition, if the speed falls on the way after the flying body 10 is launched vertically upward, the speed detection control unit 25 detects the speed. When this speed falls below a predetermined speed, a control signal is sent from the motor drive control unit 22 of the flying object control unit 18 to the rocket motor 17 so that the rocket motor 17 is ignited. 10 will fly.

  According to this embodiment, at least immediately after launching, the rocket motor mounted on the flying object is not used, and the flying object is launched in the vertical direction by the launching mechanism provided in the launching device on the ground. Therefore, it is possible to reduce the amount of fuel mounted on the flying body. Therefore, combined with the provision of the side thrusters, the turning radius of the flying object can be reduced. Therefore, it becomes possible to change the direction in a desired direction in a short time from the launch.

  If it is known in advance that the target is a relatively low altitude, it is also possible to control the direction of the aircraft when launching the flying object by providing a projection on the tail of the flying object as described below. Is possible.

  That is, the protrusions 14 c and 14 d are provided on the tail portion of the flying body 10. Then, engaging portions 45a and 45b are provided at the upper portions of the side support portions 44a and 44b of the firing mechanism 43 so as to hit the projections 14c and 14d when protruding. The engaging portions 45a and 45b are movable in the lateral direction.

  For example, if it is desired to turn the flying object 10 in the right direction in FIG. 6, the flying object is launched vertically upward with the engaging portion 45b protruding.

  Then, the engaging part 45b in the protruding state comes into contact with the protrusion 14c of the flying body 10, and the posture is changed by the force received from the protrusion 14c. In this way, it is possible to easily change the direction of the flying object without using the thruster shown in FIG. This modification is effective when the target direction and altitude are detected when the flying object is launched. This embodiment is particularly effective when the target altitude is low.

  In this embodiment, the side thruster is provided in front of the front wing. Therefore, there is an advantage that it is easy to change the flying direction of the flying object with a small turning radius.

  In the above embodiment, the flying object is described as being launched vertically upward. However, the flying object is not necessarily vertical, and the present invention can also be applied to a flying object launched nearly vertically.

  According to the above-described embodiment, it is possible to obtain a vertical launch vehicle and its launching device that have a small turning radius and that are easy to fly toward a target in an almost nearly horizontal direction at an early stage.

  Although several embodiments of the present invention have been described, these embodiments are presented by way of example and are not intended to limit the scope of the invention. These novel embodiments can be implemented in various other forms, and various omissions, replacements, and changes can be made without departing from the scope of the invention. These embodiments and modifications thereof are included in the scope and gist of the invention, and are included in the invention described in the claims and the equivalents thereof.

DESCRIPTION OF SYMBOLS 10 ... Flying object 11 ... Body 12 ... Head 13 ... Rear 14a ... Front wing 14b ... Rear wing 14c, 14d ... Projection 15... Side thrusters 15 a, 15 b, 15 c, 15 d... Nozzle 16... Gas generating section 16 a, 16 b, 16 c, 16 d ... Gas compartment 17 ... Rocket motor 18. ··· Flying object control unit 21 ··· Target detection unit 22 · · · Motor drive control unit 23 · · · Gas generation control unit 24 · · · Time measurement unit 25 · · · Speed detection control unit 26 .... Attitude detection unit 27 .... Main control unit 31 ... Flying body launching device 32 ... Support body 33 ... Launching mechanism 34 ... Placement unit 35 ... ... Gas generator 36 ... Ignators 44a, 44b ... Side support Part 45a, 45b ···· engaging portion

Claims (8)

A body part, a head part provided in front of the body part, a rear part provided behind the body part, a rocket motor provided in the rear part for generating propulsive force, and a gas provided in the body part A flying body that has a side thruster that injects gas and a gas generation unit that supplies gas to the side thruster and is launched vertically upward by a launching device,
A vertical launch vehicle characterized by being launched by a launch mechanism provided in the launcher when launched.   The vertical launch vehicle according to claim 1, wherein the vertical launch vehicle is propelled by the rocket motor after being launched vertically upward by the launch mechanism.   3. The vertical launch vehicle according to claim 2, wherein a plurality of the side thrusters are provided around the trunk of the vertical launch vehicle.   The vertical launch vehicle according to claim 3, wherein the side thruster injects the gas generated in the gas generation unit to the outside by a nozzle provided in the body unit.   The vertical projectile according to claim 4, wherein the flying body has a front wing and a rear wing, and a side thruster is provided in front of the flying body. A body part, a head part provided in front of the body part, a rear part provided behind the body part, a rocket motor provided in the rear part for generating propulsive force, and a gas provided in the body part A launching device for launching a vertical launching object having a side thruster for injecting a gas and a gas generation unit for supplying gas to the side thruster vertically upward,
When the vertical projectile is fired, the projectile is fired by a launch mechanism provided in the launcher.   The vertical launch vehicle launching apparatus according to claim 6, wherein the launching mechanism includes a gas generator. The launch mechanism includes a support that supports the vertical launch vehicle;
The launcher for a vertical projectile according to claim 7, further comprising: a mounting table on which the vertical projectile is mounted; and a gas generator that moves the mounting table upward with gas.

Images