JP2008190474A - Movable nozzle drive device and rocket motor - Google Patents

Abstract

<P>PROBLEM TO BE SOLVED: To provide a movable nozzle drive device and a rocket motor capable of materializing increase of propellant mounting quantity by miniaturization and reduction of weight in addition to securing serviceability of thrust direction control. <P>SOLUTION: The movable nozzle drive device for a solid rocket motor 1 including a movable nozzle 2 is provided with: a linear actuator 10 provided with a housing 12 and a ball screw 13 and telescopically operating between a support part 3a of a joint holder 3 side of the solid rocket motor 1 and a support part 2a of the movable nozzle 2 side; a spherical bearing 20 connecting the ball screw 13 and the support part 2a of the movable nozzle 2 side in such a manner that the same can perform self-alignment with an axis in a direction crossing a machine axis CL held as an axis; and a spherical bearing member 30 connecting the housing 12 and the support part 3a on the joint holder 3 side by fitting in such a manner that the same can perform self-alignment with the housing 12 with a center axis L of the linear actuator 10 set as an axis and can input axial load. <P>COPYRIGHT: (C)2008,JPO&INPIT

Description

  The present invention relates to a movable nozzle driving device and a rocket motor which are used to change the thrust direction by deflecting the movable nozzle in a solid rocket motor having a movable nozzle, for example.

  The movable nozzle of the solid rocket motor as described above is assembled through a flexible joint formed by laminating a large number of elastic bodies and metals on a joint holder on the solid rocket motor main body side.

  Examples of the driving device that deflects the movable nozzle to change the thrust direction include, for example, a linear actuator that includes a cylinder portion and an output shaft portion and operates to expand and contract, an output shaft portion of the linear actuator, and a support point on the movable nozzle side. There are shaft side spherical bearings that can be connected in a self-aligning manner, and cylinder side spherical bearings that connect the cylinder part of the linear actuator and the joint holder on the rocket motor body side in a self-aligning manner (for example, non- In addition, there is also a type that uses a trunnion structure to connect the cylinder portion of the linear actuator to the joint holder on the rocket motor main body side.

Such a drive device is arranged between the joint holder on the rocket motor side and the movable nozzle and at two positions in the circumferential direction with an interval of 90 ° between each other, and each linear actuator drives the movable nozzle to deflect it. The direction of thrust is changed by doing.
Space Science Research Institute Report, Special Issue No. 47, March 2003, pp. 230-234, “Thrust Direction Control (TVC) Device for MV Type Rocket”

  However, in the above-described conventional movable nozzle drive device, for convenience of positioning the axial side spherical bearing and the cylinder side spherical bearing at both ends of the linear actuator, that is, the components of the drive device are arranged in series in the axial direction. For this reason, there is a limit to miniaturization in order to ensure the operability of thrust direction control with a movable nozzle, and there is a problem that the amount of propellant loaded must be reduced by the amount that the drive device cannot be miniaturized. .

  On the other hand, in the drive device adopting the trunnion structure to connect the cylinder portion of the linear actuator to the joint holder on the rocket motor main body side, although the axial dimension of the drive device can be reduced, the support portion of the trunnion Is offset with respect to the cylinder part of the linear actuator, the radial bearing arranged to cancel the bending load is enlarged, and as a result, there is a problem that the whole apparatus is enlarged. Solving the problem has been a conventional problem.

  The present invention has been made paying attention to the above-described conventional problems, and it is possible to reduce the size and weight and increase the propellant loading amount while ensuring the operability of thrust direction control. It aims at providing a movable nozzle drive device and a rocket motor.

  The present invention is a movable nozzle driving device for a rocket motor having a movable nozzle, and includes a cylinder portion and an output shaft portion, and is operated to expand and contract between a support point on the rocket motor side and a support point on the movable nozzle side. A linear actuator that changes the distance between the two support points, and one of the cylinder part and the output shaft part of the linear actuator and one of the support point on the rocket motor side and the support point on the movable nozzle side in the direction intersecting the axis. A spherical bearing that is connected so that it can be self-aligned with the shaft as the axis, and a center of the linear actuator that is the center axis, and can be automatically aligned with the other of the cylinder part and output shaft part so that axial load input is possible And connecting the other of the cylinder part and the output shaft part to the other of the support point on the rocket motor side and the support point on the movable nozzle side. And characterized in that a configuration that includes a bearing member, and a means for solving the conventional problems described above the configuration of the movable nozzle drive unit.

  On the other hand, in the rocket motor having the movable nozzle of the present invention, the movable nozzle drive device is provided at two locations in the circumferential direction between the support point on the rocket motor side and the support point on the movable nozzle side and at an interval of 90 ° from each other The structure of the rocket motor is used as a means for solving the above-described conventional problems.

  In the present invention, the spherical bearing member is fitted to the other one of the cylinder portion and the output shaft portion of the linear actuator so as to be capable of self-alignment and capable of axial load input, and thus has a degree of freedom in driving the movable nozzle. However, as compared with the conventional drive device in which the spherical bearings are positioned at both ends of the linear actuator, the size can be reduced, and the amount of propellant loaded can be increased accordingly.

  According to the present invention, since it is configured as described above, it is possible not only to ensure the operability of thrust direction control, but also to realize an increase in the amount of propellant loaded by reducing the size and weight. There is a very good effect.

  In the movable nozzle drive device of the present invention, the output shaft portion of the linear actuator and the support point on the movable nozzle side are connected via a spherical bearing, and the cylinder portion of the linear actuator and the rocket motor side are connected via a spherical bearing member. It is possible to employ a configuration in which the supporting points are connected to each other.

  In the movable nozzle driving device of the present invention, the cylinder portion of the linear actuator and the support point on the rocket motor side are connected via a spherical bearing, and movable with the output shaft portion of the linear actuator via a spherical bearing member. The structure which has connected the support point by the side of a nozzle is employable.

  In the movable nozzle driving device of the present invention, a three-phase DC brushless motor can be used as a driving source for the linear actuator, and the rotation of the motor is converted into a linear motion by a ball screw. In this case, in order to prevent the cylinder portion and the output shaft portion of the linear actuator from rotating with each other due to the reaction force of the motor, a detent structure is required.

  EXAMPLES Hereinafter, although an Example demonstrates this invention still in detail, this invention is not limited to a following example.

  1 and 2 show an embodiment of the movable nozzle driving device of the present invention.

  As shown in FIG. 1, in a partially shown solid rocket motor 1, the movable nozzle 2 is assembled to a joint holder 3 on the main body side of the solid rocket motor 1 via a rubber joint 4.

  The drive device that deflects the movable nozzle 2 of the solid rocket motor 1 and changes the thrust direction includes a linear actuator 10 positioned between the joint holder 3 on the main body side of the rocket motor 1 and the movable nozzle 2, and this linear actuator Reference numeral 10 denotes a motor 11, a housing 12 as a cylinder part integrally assembled with the motor 11, a nut (not shown) that is housed in the housing 12 and is rotated by the output of the motor 11, and the nut and screw A ball screw 13 serving as an output shaft portion that is coupled to convert the rotation of the motor 11 into a linear motion, and a detent key 14 that prevents the housing 12 and the ball screw 13 from rotating with each other due to the reaction force of the motor 11 are provided. ing.

  In addition, the drive device includes a spherical bearing 20 that connects the end of the ball screw 13 of the linear actuator 10 to a support portion (support point) 2a on the movable nozzle 2 side, and a housing 12 of the linear actuator 10 that is a main body of the rocket motor 1. A spherical bearing member 30 connected to the joint holder 3 on the side is provided.

  The spherical bearing 20 connects the end portion of the ball screw 13 and the support portion 2a on the movable nozzle 2 side so as to be capable of self-alignment with an axis in a direction intersecting the machine axis CL as an axis, while the spherical bearing member 30 is The joint 12 is fixed to the support portion (support point) 3a of the joint holder 3 and is fitted to the housing 12 so that the center axis L of the linear actuator 10 can be automatically aligned with the housing 12 so that axial load input is possible. The holder 3 is connected, and thereby, the degree of freedom in driving the movable nozzle 2 is ensured. The axial center of the spherical bearing 20 is along a direction orthogonal to the machine axis CL in a state where the movable nozzle 2 is not deflected.

  As shown in FIG. 2, the drive device described above is disposed between the joint holder 3 and the movable nozzle 2 on the main body side of the rocket motor 1 and at two circumferential positions at a 90 ° interval. The position detectors 5 for detecting the nozzle rudder angle are respectively arranged in the portions facing each other with the drive device and the axle CL in between.

  In this drive device, when a command to change the thrust direction is given, a motor drive signal is output to the linear actuator 10 and is movable by the linear motion of the ball screw 13 by the rotation of the motor 11, that is, by the expansion and contraction operation of the linear actuator 10. A control moment is obtained by driving the nozzle 2 to change the thrust direction.

  In the drive device described above, the spherical bearing member 30 is fitted to the housing 12 of the linear actuator 10 so as to be capable of self-alignment and capable of axial load input. Compared with the conventional drive device in which the bearings are positioned at both ends of the linear actuator, the size can be reduced, and the amount of propellant loaded can be increased by that amount, or other equipment can be equipped. .

  In this embodiment, the case where the output shaft portion that converts the rotation of the motor 11 into linear motion is the ball screw 13 is shown. However, the present invention is not limited to this, and other configurations include, for example, a ball screw. 13 can be fixed to the housing 12 side, and a ball nut screwed to the ball screw 13 can be used as an output shaft portion that converts the rotation of the motor 11 into linear motion.

  FIG. 3 shows another embodiment of the movable nozzle driving device of the present invention.

  As shown in FIG. 3, the movable nozzle driving device in this embodiment is different from the movable nozzle driving device in the previous embodiment in that the housing 12 of the linear actuator 10 and the rocket motor 1 are connected via a spherical bearing 20. The joint holder 3 side support portion (support point) 3a is connected, and the ball screw 13 of the linear actuator 10 and the movable nozzle 2 side support portion (support point) 2a are connected via a spherical bearing member 30. Therefore, other configurations are the same as those of the movable nozzle driving device according to the previous embodiment.

  In the driving apparatus in this embodiment, the spherical bearing member 30 is fitted to the ball screw 13 of the linear actuator 10 so as to be capable of self-alignment and capable of axial load input, and thus has a degree of freedom for driving a movable nozzle. However, compared with the conventional drive device in which the spherical bearings are positioned at both ends of the linear actuator, the size can be reduced, and the amount of propellant loaded can be increased by that amount, or other equipment can be equipped. It will be possible.

  In the above-described embodiments, the case where the movable nozzle driving device of the present invention is employed in a solid rocket motor having a movable nozzle is shown, but the present invention is not limited to this.

It is a partial expanded sectional explanatory view in the movable nozzle attachment part of the solid rocket motor which shows one Example of the movable nozzle drive device which concerns on this invention. (Example 1) It is the partial side explanatory drawing (a) of the solid rocket motor which shows simply the arrangement | positioning condition in the solid rocket motor of the drive device of FIG. 1, and the cross-sectional explanatory drawing (b) in a movable nozzle part. (Example 1) It is a partial expanded cross-section explanatory drawing in the movable nozzle attachment part of the solid rocket motor which shows the other Example of the movable nozzle drive device which concerns on this invention. (Example 2)

Explanation of symbols

1 Solid Rocket Motor 2 Movable nozzle 2a Movable nozzle side support (support point)
3 Joint holder 4 Rubber joint 5 Position detector 3a Joint holder side support (support point)
10 Linear actuator 11 Motor 12 Housing (cylinder part)
13 Ball screw (output shaft)
14 Non-rotating key 20 Spherical bearing 30 Spherical bearing member CL Machine axis L Center axis of linear actuator

Claims (4)

A movable nozzle driving device for a rocket motor having a movable nozzle,
A linear actuator that includes a cylinder part and an output shaft part, and expands and contracts between a support point on the rocket motor side and a support point on the movable nozzle side to change the distance between the two support points;
One of the cylinder and output shafts of the linear actuator and one of the support point on the rocket motor side and one of the support points on the movable nozzle side are connected in a self-aligning manner with the axis in the direction intersecting the machine axis as the axis. And spherical bearings
Centering on the central axis of the linear actuator, the other of the cylinder part and output shaft part can be automatically aligned with the other of the cylinder part and output shaft part, and the other one of the cylinder part and output shaft part can be fitted to the rocket motor side. A movable nozzle drive device comprising a spherical bearing member that connects the other support point and the other support point on the movable nozzle side. The output shaft portion of the linear actuator and the support point on the movable nozzle side are connected via a spherical bearing, and the cylinder portion of the linear actuator and the support point on the rocket motor side are connected via a spherical bearing member. The movable nozzle drive device according to claim 1. The cylinder part of the linear actuator and the support point on the rocket motor side are connected via a spherical bearing, and the output shaft part of the linear actuator and the support point on the movable nozzle side are connected via a spherical bearing member. The movable nozzle drive device according to claim 1. In a rocket motor having a movable nozzle, the movable nozzle driving device according to any one of claims 1 to 3 is arranged between the support point on the rocket motor side and the support point on the movable nozzle side and at intervals of 90 ° from each other. A rocket motor characterized by being arranged in two places in the circumferential direction.

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