KR101995518B1 - Fixing detent structure and Rocket having the same - Google Patents

Abstract

The present invention relates to rocket technology, and more specifically, to a rocket fixing detent structure applied to a rocket mounted on an air launched platform to be launched and a rocket having the same. The fixing detent structure of the present invention includes a substrate, a detent device, a compressive force adding device, and a posture control support device.

Description

[0001] DESCRIPTION [0002] Fixed detent structure and rocket having same [0003]

The present invention relates to rocket technology, and more particularly, to a detent structure for rocket fixation applied to a rocket mounted on a launch platform and to a rocket having the detent structure.

The rocket mounted on the air launch platform is normally launched using the initial trajectory holding rails, and the rocket must be stably fixed to the rail through a fixture (detent mechanism) before launch. That is, the detent mechanism is released at the time of firing, and is accelerated by the thrust force to fly out of the rail at a stable speed.

Therefore, it is important to stably fix / separate the rocket to the foot use rail, and various detent mechanisms (electric fixation system, pyrobolt fixation system, mechanical fixation system, etc.) may be applied.

The rocket detent mechanism mounted on the air launch platform may affect the viability of the expensive air launch platform in case of abnormal operation, so stable operation is essential. In addition, airborne launch platforms operating at high flight altitudes (low temperature environments) can have a significant impact on the operating reliability of the part due to the operating environment (temperature).

Therefore, it is particularly important to design reliable system components with high reliability and high reliability. In consideration of this, a mechanical type having a relatively low influence of a temperature environment and a relatively high operating reliability is preferred, and a pushing mechanism thrust of a rocket is utilized for operation of the detent mechanism.

In addition, stable operation is essential because, in the case of abnormal operation, it can affect the viability of expensive airborne launch platforms. In addition, airborne launch platforms operating at high flight altitudes (low temperature environments) can have a significant impact on the operating reliability of the part due to the operating environment (temperature). Therefore, it is particularly important to design reliable system components with high reliability and high reliability.

1. Korean Published Patent No. 1983-0001582 2. U.S. Patent No. 7,624,947 B2 3. U.S. Patent No. 7,665,395 B2

It is an object of the present invention to provide a detent structure for locking and releasing a rocket on a foot using rail, and a rocket having the detent structure.

In order to achieve the above-mentioned object, the present invention provides a fixing detent structure for securing and reliably releasing a rocket to a foot use rail.

Wherein the fixing detent structure comprises:

A substrate sliding on the rail;

A detent device formed on one surface of the substrate, the detent device being fixed to the rail;

A compressing force applying device formed on the other surface of the substrate and applying a preload or compressive force to restrain or release the rail by thrust; And

And an attitude control support device having one end connected to the detent device and the other end connected to the compression force addition device to perform posture control in the horizontal direction or the upward direction.

Here, the detent device may include a detent for supporting a load in contact with a hanger formed on the rail, And a restraint inducing support for restraining the conveying or rotating movement of the detent.

The detent may be constrained by a constraint inducing pin that is inserted into first guide holes formed on both sides of the constraint inducing support.

In addition, the first guide hole may have a one-letter shape so that the detent moves in the lateral direction.

In addition, the constraint inducing pin may have a cylinder-shaped planar shape so as to independently restrict the transfer and rotation motion of the detent.

The detent may be constrained by an attitude control pin inserted into a second guide hole formed on both sides of the attitude control and supporting device.

The second guide hole may have an inverted U-shape so that the detent moves in one of a transverse direction and a longitudinal direction.

The compression force addition device may further include: a rotation hinge housing; And a rotation support restricting portion formed on the surface of the substrate and restricting rotation of the rotation hinge housing through compression spring hinges formed on both sides thereof.

At this time, the rotary hinge housing includes a compression spring; A preload nut for adjusting a preload to the compression spring; And a pressing shaft member for restricting the operation of the detent through the compression spring.

Further, the end of the pressure shaft member is connected to the end of the detent by the posture control pin.

Further, the compression spring may be characterized in that a plurality of dish springs are connected in series.

The position of the compression spring hinge may be a rotation point of the compression spring hinge offset to perform an irreversible function to prevent accidental restoration after the detent is released.

The compression spring hinge point of the compression spring hinge may be a point where a line passing through a center axis of the rotary hinge housing and a pressing shaft member and a vertical line passing through a rotation point of the compression spring hinge meet.

In addition, the spring compression force of the compression spring at which the detent starts to be released may be determined according to the characteristics of the thrust.

The spring compression force of the compression spring in which the release of the detent is started to prevent irreversible operation of the detent may be greater than the spring compression force in a state in which the detent is completely released .

On the other hand, an embodiment of the present invention can provide a rocket in which the abovementioned fixing detent structure is installed on one side.

 According to the present invention, the detent mechanism for fixing the rocket can stably control the binding force with the kinematic elements (the posture control support portion and the constraint induction support portion) that sequentially control the transfer and the rotary motion.

In addition, as another effect of the present invention, the compression force and the pre-pressurizing device allow stable binding force to be applied to the rocket mounted and operated on the air launch platform, and stable binding force can be relaxed by the launch procedure, Can contribute.

Further, another effect of the present invention is that a load attaching device for separate restraint and / or control is not required.

Further, as another effect of the present invention, it is possible to accurately measure and control the restraint load by realizing the restraining load by the kinematic linear motion, so that it is relatively reliable and contributes to the reduction of the production cost of the product due to simplification of the restraint .

1 is a conceptual view of a rocket having a fixing detent structure according to an embodiment of the present invention.
2 is an enlarged view of the fixturing detent structure 130 shown in FIG.
3 is a detail enlarged view of the fixing detent structure 130 shown in FIG.
FIG. 4 is a perspective view showing the fixed detent structure 130 shown in FIG. 2 in an unlocked state.
5 is an operational conceptual diagram of the fixture detent structure 130 shown in FIG.
6 is a graph showing the operating force concept of the fixing detent structure according to an embodiment of the present invention.

While the invention is susceptible to various modifications and alternative forms, specific embodiments thereof are shown by way of example in the drawings and will herein be described in detail. It is to be understood, however, that the invention is not to be limited to the specific embodiments, but includes all modifications, equivalents, and alternatives falling within the spirit and scope of the invention.

Like reference numerals are used for similar elements in describing each drawing.

The terms first, second, etc. may be used to describe various components, but the components should not be limited by the terms. The terms are used only for the purpose of distinguishing one component from another.

For example, without departing from the scope of the present invention, the first component may be referred to as a second component, and similarly, the second component may also be referred to as a first component. The term "and / or" includes any combination of a plurality of related listed items or any of a plurality of related listed items.

Unless otherwise defined, all terms used herein, including technical or scientific terms, have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs.

Terms such as those defined in commonly used dictionaries are to be interpreted as having a meaning consistent with the contextual meaning of the related art and are to be interpreted as either ideal or overly formal in the sense of the present application Should not.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, a lock detent structure and a rocket having the lock detent structure according to an embodiment of the present invention will be described in detail with reference to the accompanying drawings.

1 is a conceptual view of a rocket having a fixing detent structure according to an embodiment of the present invention. In particular, FIG. 1 is a general conceptual diagram of a launch pad 100 and a launch pad rail 20 for an air launch platform including a fix detent structure 130.

Referring to FIG. 1, a fixing detent structure 130 for fixing the launching rail 20 and the rocket 100 to the launching rail 20 is required for stable fixing and firing of the rocket 100. On the other hand, the rocket 100 is normally attached to the front hanger 111 and the rear hanger 112 and guided by the rail 20 to leave the air launch platform.

At this time, the fixing detent structure 130 fixes the rocket 100 during storage and transportation, and when the rocket 100 is released from the rocker 100 by an appropriate method, .

2 is an enlarged view of the fixturing detent structure 130 shown in FIG. 2 is a perspective view illustrating a detent structure 130 according to an embodiment of the present invention and a front hanger 111 for using the rocket 100 and the rocket 100 as support points for supporting the rail 20 And a rail 20. As shown in Fig.

Referring to FIG. 2, the fixing detent structure 130 includes a detent device 210 for fixing and an additional device 220 for applying a preload and a compressive force. The detent device 210 includes: Is fixed to the rail (20). The rocket 100 is fixed to the rail 20 by using the hanger 111 fixed to the rocket 100 by the role of the detent structure 130 for fixing the rocket.

When the thrust is actuated by the propelling engine operation of the rocket 20, the rocket 100 is released from the rail 20 and is released from the fixed state due to the role of the fixing detent structure 130.

3 is a detail enlarged view of the fixing detent structure 130 shown in FIG. Referring to FIG. 3, the fixing detent structure 130 includes a detent device 210 for fixing and a compression force applying device 220 for applying a preload and a compressive force.

The detent device 210 includes a substrate 300 that slides on the rail 20, a detent 311 that is in contact with the hanger 111 formed on the rail 20 to support a load, A restraint inducing support 312 for restraining the transfer and rotation of the detent 311 and a restraint inducing pin 313 for restraining the detent 311 to the restraint inducing supporter 312 As shown in FIG. The restraint inducing pins 313 are inserted into the guide holes 312-1 formed on both sides of the restraint inducing supporter 312 to restrain the detent 311. [ The constraint inducing pin 313 moves from the point P to the point P 'or moves from the point P' to the point P along the guide hole 312-1.

An attitude control support device 314 for connecting the detent 311 and the preloading and compressing force adding device 320 and controlling the posture of the two components is constructed. Guide holes 314-1 are formed on both side surfaces of the posture control support device 314. [ The posture control pins 315 are inserted into the guide holes 314-1 formed on both sides of the restraint posture control support device 314 to restrain the detent 311. [ The posture control pin 315 moves from the point P 'to the point P' from the point P 'to the point P' 'along the guide hole 314-1, or from the point P' to the point P ' do.

That is, one of the detents 311 is restrained by the restraint inducing pin 313, and the other is restrained by the attitude control pin 315. In particular, since the guide hole 312-1 has a straight shape, the detent 311 moves only in the horizontal direction by the guide hole 312-1. That is, the detent 311 is restricted to move back and forth only. On the other hand, since the guide hole 314-1 has a shape of an inverted "? &Quot; shape, the detent 311 moves in the lateral direction by the guide hole 314-1 and moves in the longitudinal direction. In other words, it is possible to move up and down while moving forward and backward.

 As shown in the enlarged view, the constraint inducing pin 313 has a cylinder-shaped planar machined shape for independently restricting the feed and rotary motion. The restraint inducing supporter 312 has a guide hole 312-1 in which a mobile slot and a rotation hole are machined so as to realize this.

The compression force addition device 220 for applying a preload and a compression force is composed of a compression spring 322 having a plurality of diaphragm springs having a high elastic modulus connected in series and a preload nut 323 for applying a preload to the compression spring 322, A pressing shaft member 326 connected to the attitude control pin 315 and restraining the movement of the detent 311 through the compression spring 322, a rotary hinge housing 321 to which the pressing shaft member 326 and the rotary hinge housing 321 are assembled, And a rotation support restricting portion 324 for restricting the rotation of the rotation support portion 324. On both sides of the rotation support restricting portion 324, a compression spring hinge 325 for supporting the rotation of the rotation hinge housing 321 is formed.

3, when the hanger 111 of the rocket 20 is in a fixed state, the restraint inducing pin 313 is located at the point P, and in this state, the compression spring 322 is in the pre- .

FIG. 4 is a perspective view showing the fixed detent structure 130 shown in FIG. 2 in an unlocked state. Referring to Fig. 4, Fig. 4 shows a state in which the hanger 111 is completely released from the constraint of the detent 311. Fig. The detent 311 and the pressing shaft member 326 are pressed against the detent 311 through the hanger 111 when the thrust by the propelling engine (not shown) of the rocket 20 acts on the detent 311 through the hanger 111, 322 and the point P and the point P1 are respectively guided to the point P 'and the point P1 "by the kinematic role of the constraint inducing pin 313, the constraint inducing supporter 312 and the attitude control support apparatus 314 The restraint inducing pin 313 linearly moves laterally from the point P to the point P 'in the case of the restraint inducing supporter 312. On the other hand, in the case of the attitude control support device 314, Moves from the point P1 to the point "P1 " in the horizontal direction, and then moves in the vertical direction.

The magnitude of the load for releasing the detent 311 at this time depends on the length of the linear slot formed in the guide hole 312-1 of the constraint inducing support 313 and the elastic modulus of the compression spring 322, (323). ≪ / RTI >

The detent 311 rotates around the point P 'by the moment acting on the contact point between the detent 311 and the front hanger 111 and the offset distance between the rotation hinge P1' 111).

In this state, the spring force exerts a force to keep the detent 311 in the released state by the influence of the rotary hinge 325, which is the center of rotation of the compression force addition device 320 that adds the preload and the compressive force. This will be described later with reference to FIG.

5 is an operational conceptual diagram of the fixture detent structure 130 shown in FIG. 5, when the thrust is applied to the detent 311 through the hanger 111, a restraint inducing pin (not shown) fixed to the detent 311 against the compressive force acting through the pressing shaft member 326 313 and the posture control pin 315 are moved from P point to P1 and from P 1 to P 1 by the mechanical constraint of the posture control support device 314 and the constraint induction support part 312 Move.

The moment generated by offsetting the contact point between the detent 311 and the hanger 111 from the point P ', which is the rotational hinge, rotates the detent 311 around the point P'. When the point P1 is reached, the hanger 111 is released from the constraint of the detent 311, and the rocket 20 freely advances by the thrust force. On the other hand, the center locus connecting the points P1 'and P' Should be part of an arc centered at point P '.

5 is a rotation point of the compression spring hinge 325. A point Q1 is a line passing through the center axis of the rotary hinge housing 321 and the pressing shaft member 326 and a line passing through the point Q2, This is a meeting point. Here, when the compression spring hinge point of the compression spring hinge 325 is Q1, the point P1 'and the point P1 "are positions where the same compression force acts. Therefore, after the detent 311 is released from the restraint, The detent 311 may be returned to the P1 position across P1 'due to a slight external force acting on the detent 311 after the point 315 reaches the point P1', which may interfere with the progress of the rocket.

Therefore, it is important to prevent the detent 311 from returning to its original position. The position of the compression spring hinge 325 of the rotary hinge housing 321 is set such that the distance between the P1 'and the Q2 is smaller than the distance between the P1' and the Q2. Q2 is offset from the point Q1 passing through the center line by a certain distance therefrom.

6 is a graph showing the operating force concept of the fixing detent structure according to an embodiment of the present invention. Referring to FIG. 6, the force generating concept of the fix detent structure 130 is shown. 6, the horizontal axis shows a change in the force acting on the posture control pin 315 at the points P1, P1 ', and P1 ". The vertical axis shows the spring compression force of the compression spring 322. FIG.

In the P1 state (fixed state), F_P1 always acts (610) due to the preload acting on the compression spring 322, F_P1 'acts at the point P1' where the detent 311 is released, Quot; F_P1 "less than F_P1 ' by the offset arrangement of the compression spring hinge 325 already mentioned.

It can be seen that the irreversibility of the detent mechanism is realized by the difference ΔF between the two forces. That is, it is difficult for the posture control pin 315 to return to P1 through P1 '(620) by implementing the offset period 630 corresponding to the difference ΔF between the two forces. That is, the normal detent structure (130 in FIG. 1) should prevent the rocket (20 in FIG. 1) from moving during a handling operation in which thrust does not act. This can be realized by adjusting the preload F_P1 applied through the preload nut 323 and the spring compression force F_P1 'at which the detent 311 starts to be released is determined in consideration of the characteristics of the thrust force.

20: Rail
100: Rocket
111,112: Hanger
130: fixed detent structure
210: Detent device
220: Compression force addition device
311: Detent 312: Restraint induction support
313:
314: Posture control support device 315: Posture control pin
321: Rotating hinge housing 322: Compression spring
323: Preload nut 324:

Claims (14)

A substrate (300) sliding on the rail (20);
A detent device 210 formed on one surface of the substrate 300 and fixed on the rail 20;
A compressing force applying device 220 formed on the other surface of the substrate 300 and applying a preload or compressive force to restrain or release the rail 20 from the rail 20 by thrust; And
An attitude control support device 314 having one end connected to the detent device 210 and the other end connected to the compression force addition device 220 to perform attitude control in the horizontal direction or the upward direction;
Wherein the detent structure comprises:
The method according to claim 1,
The detent device 210 includes:
A detent 311 for supporting a load in contact with the hanger 111 formed on the rail 20; And
And a restraint inducing support part (312) for restricting the conveying or rotating movement of the detent (311). 3. The method of claim 2,
The detent 311 is constrained by a restraint inducing pin 313 that is inserted into a first guide hole 312-1 formed on both sides of the restraint inducing supporter 312. [ rescue.
The method of claim 3,
Wherein the first guide hole (312-1) has a one-letter shape so that the detent (311) moves in the horizontal direction.
3. The method of claim 2,
Wherein the detent 311 is restrained by an attitude control pin 315 inserted into a second guide hole 314-1 formed on both sides of the attitude control support device 314. [ Tent structure.
6. The method of claim 5,
Wherein the second guide hole (314-1) has an inverted U-shape so that the detent (311) moves in either the horizontal direction or the vertical direction.
6. The method of claim 5,
The compression force addition device (220)
A rotary hinge housing (321); And
And a rotation support restricting portion (324) formed on the surface of the substrate (300) and restricting rotation of the rotation hinge housing (321) through compression spring hinges (325) formed on both sides thereof,
The rotary hinge housing 321 includes a compression spring 322; A preload nut 323 for adjusting a preload to the compression spring 322; And a pressing shaft member (326) for restricting the operation of the detent (311) through the compression spring (322).
8. The method of claim 7,
And the end of the pressing shaft member (326) is connected to the end of the detent (311) by the posture control pin (315).
8. The method of claim 7,
Characterized in that the compression spring (322) is in the form of a plurality of diaphragm springs connected in series.
8. The method of claim 7,
The position of the compression spring hinge 325 is determined by the rotation point Q2 of the compression spring hinge 325 offset 630 to perform an irreversible function to prevent accidental restoration after the detent 311 is released. Wherein the detent structure for fixing comprises:
11. The method of claim 10,
The compression spring hinge point Q1 of the compression spring hinge 325 is connected to a line passing through the center axis of the rotary hinge housing 321 and the pressing shaft member 326 and a line passing through the rotation point Q2 of the compression spring hinge 325, Is a point at which a vertical line passing through the fixing detent structure meets.
8. The method of claim 7,
Wherein the spring compression force of the compression spring (322) from which the detent (311) starts to be released is determined according to the characteristics of the thrust.
8. The method of claim 7,
The spring compression force of the compression spring 322 in which the release of the detent 311 is started to prevent the detent 311 from irreversibly operating is determined by the spring compression force of the compression spring 322 in a state where the release of the detent 311 is completed Wherein the spring force is larger than the spring compressive force.
A rocket comprising a detent structure (130) according to any one of claims 1 to 13 on one side.

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