JP7136664B2 - rocket - Google Patents

Description

The present invention relates to improvements in rockets equipped with thrust direction control devices.

As described in Non-Patent Document 1, there are various types of thrust direction control devices for rockets, and a representative example is a movable nozzle. This thrust direction control device has a nozzle that can swing with respect to the fuselage, and by changing the direction of the nozzle to change the thrust direction, a control moment is obtained, and an aerodynamic moment is generated in the fuselage during flight. In order to stabilize the airframe, the thrust direction (rudder angle) is changed to cancel out this aerodynamic moment.

``Aerospace Engineering Handbook'' Maruzen, Dec. 20, 1974, p. 652

By the way, in the conventional rockets described above, when the aerodynamic moment is large, such as at maximum dynamic pressure, the rudder angle of the thrust direction control is increased to offset the aerodynamic moment, and there is a risk of deviation from the rocket specifications. be. Therefore, as a measure to mitigate the aerodynamic force, it is conceivable to reduce the aerodynamic moment by placing flares at the tail of the aircraft to move the center of aerodynamic force back toward the center of gravity. However, deploying flares increases air resistance and speed loss, which reduces the launch capability (the payload mass that can be carried).

SUMMARY OF THE INVENTION It is an object of the present invention to provide a rocket capable of both suppressing the necessary steering angle for thrust direction control and reducing speed loss due to air resistance. and

The rocket according to the present invention includes a thrust direction control device, a pressure sensor arranged on the side of the fuselage, and a movable flare arranged on the tail of the fuselage and operating from a stowed position along the side of the fuselage to a deployed position outside the fuselage. It is characterized in that the movable flare is driven based on the magnitude of the dynamic pressure detected by the pressure sensor.

A rocket according to the present invention is launched with the movable flare in the stowed position. At this time, the rocket can be launched without speed loss because the air resistance caused by the movable flare can be ignored. After that, the rocket performs attitude control during flight with the thrust direction control device, and detects the dynamic pressure with the pressure sensor. The rocket then drives the movable flare to the deployed position when the dynamic pressure increases. As a result, the aerodynamic center of the rocket retreats closer to the center of gravity and the aerodynamic moment decreases, so the required steering angle for thrust direction control to offset the aerodynamic moment is also suppressed. Also, when the dynamic pressure drops, the rocket returns the movable flare to the stowed position to minimize speed loss due to air resistance.

In this way, the above-mentioned rocket can both suppress the necessary steering angle for thrust direction control and reduce the speed loss due to air resistance.

BRIEF DESCRIPTION OF THE DRAWINGS It is a figure explaining one Embodiment of the rocket concerning this invention, It is the perspective view (A) explaining the state which accommodated the flare, and the block diagram (B) which shows a control system. FIG. 2 is a perspective view illustrating a state in which flares of the rocket shown in FIG. 1 are deployed;

An embodiment of a rocket according to the present invention will be described below with reference to the drawings.
A rocket R shown in FIG. 1A has a body 1 composed of a propulsion engine section 1A and a payload mounting section 1B on the head side thereof. The propulsion unit 1A is a solid or liquid rocket. The payload loading section 1B is covered with a separable nose fairing.

The rocket R also has a thrust direction control device 2, a pressure sensor 3 arranged on the side of the fuselage, and a movable flare 4 arranged on the tail of the fuselage and operating from a stowed position along the side of the fuselage to a deployed position outside the fuselage. , and the movable flare 4 is driven based on the magnitude of the dynamic pressure detected by the pressure sensor 3 . Therefore, the rocket R is equipped with a flare control device 5 that drives and controls the movable flare 4 based on the dynamic pressure detected by the pressure sensor 3 .

The thrust direction control device 2 includes a movable nozzle N that is swingable with respect to the tail of the airframe 1, and includes actuators for driving the movable nozzle N and control equipment therefor, although not shown. The pressure sensor 3 is arranged on the side of the payload loading section 1B, and may be one that detects the atmospheric pressure or one that directly detects the air pressure received during flight. Pressure can be detected (calculated).

The movable flare 4 is a tubular structure composed of a plurality of flare members 4A divided around the axis of the fuselage 1 . Each flare member 4A is a plate-like member having the same size, and is rotatable in the inward and outward directions of the fuselage 1 around the respective ends on the head side of the fuselage. The number of flare members 4A is not particularly limited, and members having different dimensions and shapes may be arranged according to positions around the machine axis.

As shown in the control system of FIG. 1B, the movable flare 4 operates the flare members 4A all at once by a drive section 6 to which a command signal from a flare control device 5 is input. The drive unit 6 is composed of, for example, actuators, a power transmission mechanism, and the like.

The flare control device 5 controls the movable flare 4 to the deployed position when the dynamic pressure detected by the pressure sensor 3 is equal to or higher than the threshold, and to the retracted position when the dynamic pressure is less than the threshold. conduct. That is, the flare control device 5 drives and controls the movable flare 4 by outputting a command signal to the driving section 6 based on the magnitude of the dynamic pressure.

The rocket R described above has the center of aerodynamic force AC located on the head side with respect to the center of gravity G, and is launched with the movable flare 4 in the stowed position as shown in FIG. 1(A). At this time, the rocket R can be launched without speed loss because the air resistance caused by the movable flares 4 can be ignored.

After that, the rocket R performs attitude control during flight with the thrust direction control device 2 and detects the dynamic pressure with the pressure sensor 3 . Then, the rocket R drives the movable flare 4 to the deployment position as shown in FIG. 2 when the dynamic pressure reaches or exceeds the threshold. That is, each flare member 4A is rotated to the outside of the airframe 1 all at once.

As a result, as indicated by the arrow in FIG. 2, the aerodynamic center AC of the rocket R retreats closer to the center of gravity, the distance L between the center of gravity G and the aerodynamic center AC becomes smaller, and the aerodynamic moment decreases. is also suppressed. Further, when the dynamic pressure drops below the threshold value, the rocket R returns the movable flare 4 to the retracted position shown in FIG. 1(A) to reduce the air resistance. In other words, the rocket R deploys the movable flares 4 only when the dynamic pressure becomes high in the atmosphere to minimize speed loss due to air resistance.

In this manner, the rocket R described above can achieve both suppression of the required steering angle for thrust direction control and reduction of speed loss due to air resistance. Therefore, according to the rocket R described above, it is possible to avoid the possibility that the necessary steering angle for thrust direction control deviates from the specifications, and to maintain good launch capability (mass of payload that can be mounted).

Further, the above-mentioned rocket R employs a movable flare 4 made up of a plurality of flare members 4A, so that it is possible to obtain each state of storage and deployment with a relatively simple structure. Further, when the rocket R employs the movable flares 4, the flare members 4A or selected flare members 4A may be individually driven. As a result, the rocket R can use the flare member 4A as a moving blade as an auxiliary functional part of the thrust direction control device 2. FIG.

The configuration of the rocket according to the present invention is not limited to the above-described embodiment, and the specific structure can be changed as appropriate without departing from the gist of the present invention.

R rocket 1 fuselage 2 thrust direction control device 3 pressure sensor 4 movable flare 4A flare member 5 flare control device

Claims (3)

Equipped with a thrust direction control device, a pressure sensor placed on the side of the fuselage, and a movable flare placed on the tail of the fuselage and operating from the stowed position along the side of the fuselage to the deployed position outside the fuselage, and detected by the pressure sensor. A rocket characterized by driving a movable flare based on the magnitude of dynamic pressure. a flare control device for driving and controlling the movable flare based on the magnitude of the dynamic pressure detected by the pressure sensor;
3. The flare control device controls the movable flare to the deployed position when the dynamic pressure is equal to or higher than a threshold value, and controls the movable flare to the retracted position when the dynamic pressure is less than the threshold value. 1. Rocket according to 1. The movable flare is composed of a plurality of flare members divided around the axis of the airframe,
3. A rocket according to claim 1 or 2, wherein each flare member is rotatable about its head-side end.

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