CN113203326A

CN113203326A - Hinge structure is thrown soon to radome fairing

Info

Publication number: CN113203326A
Application number: CN202110478786.8A
Authority: CN
Inventors: 何爱颖; 陈景鹏; 张伟方; 谢雪明; 王骏来; 刘广宁
Original assignee: Beijing Xingtu Exploration Technology Co ltd
Current assignee: Beijing Xingtu Exploration Technology Co ltd
Priority date: 2021-04-28
Filing date: 2021-04-28
Publication date: 2021-08-03

Abstract

The invention discloses a fairing rotary throwing hinge structure. The hinge structure comprises a fixed support, a rotating shaft, a limiting pin, a limiting groove and the like; the fixing support is connected on the arrow body, the rotating support is fixedly connected with the half cowling of fairing, the hinge rotating shaft is connected with the fixing support, and the limiting pin is connected with the rotating support. When the half fairing rotates around the hinge under the action of separating force, when the rotation angle of the half fairing is smaller than the over-vertex angle alpha, the limiting pin on the rotating support and the limiting groove on the fixed support limit the half fairing to separate from the rotating shaft; when the half-cover rotating angle of the fairing is larger than the over-vertex angle alpha and does not reach the unhooking angle theta, a rotating hole in the rotating support needs to ensure that the thrust of the rocket body can completely act on the rotating support; after the half-cover rotating angle of the fairing passes through the unhooking angle theta, the rotating hole in the rotating support and the limiting groove in the fixed support do not interfere with the automatic separation of the half-cover of the fairing and the arrow body. Key words: the fairing, pivot, fixing support.

Description

Hinge structure is thrown soon to radome fairing

Technical Field

The invention belongs to the technical field of carrier rockets and the like, and particularly relates to a fairing rotary throwing hinge structure.

Background

The fairing for carrying rocket projectiles generally adopts a throwable structural form, after the carrier rocket flies out of the atmosphere, tasks such as load protection, rocket body appearance maintenance, aerodynamic resistance reduction and the like are completed, and in order to improve efficiency, increase the carrying capacity of the rocket and give way for a release channel of the load, the fairing needs to be thrown away. The separation of the fairing and the arrow body is divided into integral axial separation, transverse horizontal pushing separation and rotary throwing separation. The whole axial separation mode has simple structure design and few separation surfaces. However, after the bottom of the fairing is unlocked, the fairing is pushed out forwards along the axial direction, so that the separation time is prolonged, the control problem after the fairing is separated is increased, and the method is not suitable for large fairings. The fairing adopting the horizontal pushing separation mode consists of two half shrouds, and a pollution-free detonating fuse is arranged on a longitudinal separation surface. The structure can complete the unlocking and separation of the two half covers by one ignition command, has high reliability, small disturbance to a rocket and no pollution, but has difficult assembly and butt joint, larger separation energy requirement and higher cost. Two half cowlings of the fairing in a rotary-throwing separation mode are connected in the transverse direction and the longitudinal direction through explosion bolts, a movable hinge at the lower end of the fairing is hinged with a rocket body, and a spring generating separation force is arranged in the fairing. After a separation instruction is sent out, the transverse and longitudinal explosion bolts are unlocked, the spring provides separation force, the two half covers rotate around the hinge rotating shaft respectively and are separated from the rocket body, the effective volume of the fairing of the structure is larger, the flexibility of the structure of the fairing body is high, the cost is low, and most of the fairing of the current carrier rocket adopts a spin-casting separation scheme.

Disclosure of Invention

The invention provides a fairing rotary throwing hinge structure which is simple and compact in structure, high in reliability, easy to machine, install and convenient to operate.

A fairing rotary throwing hinge structure comprises a fixed support, a rotary support, a rotating shaft, a limiting pin, a limiting groove and the like;

the fixed support is arranged on the arrow body, a limit groove is formed in the fixed support, and the rotating shaft is fixed on the fixed support;

the rotating support is arranged on the half cover of the fairing, a rotating hole is designed on the rotating support, and the limiting pin is fixed on the rotating support;

when the fairing is separated, the half fairing of fairing rotates outwards around the rotating shaft by the separating force provided by the separating impulse device, and when the rotating angle of the half fairing is smaller than the vertex angle alpha, the half fairing of fairing is restrained from moving axially by the limiting pin on the rotating support and the limiting groove on the fixed support to prevent the half fairing from separating from the rotating shaft.

When the rotating angle of the half cowling of the fairing is larger than the over-vertex angle alpha, the thrust of the carrier rocket engine acts on the rotating hole of the rotating support, so that the rotating speed of the half cowling of the fairing is increased. The rotating speed of the half-cover of the fairing is increased, the centrifugal force of the half-cover of the fairing is correspondingly increased, and the half-cover of the fairing can be separated from the arrow body only when the centrifugal force is increased to overcome the component of the inertia force in the opposite direction of the centrifugal force. In the process, the rotating hole on the rotating support needs to ensure that the thrust of the arrow body can completely act on the rotating support.

When the rotation angle of the half cover of the fairing passes through the unhooking angle theta, the limiting groove and the rotating shaft on the fixed support and the limiting pin and the rotating hole on the rotating support are free of any constraint, so that the fairing is automatically separated from the hinge rotating shaft under the action of centrifugal force, and the separation from the rocket body is completed.

Drawings

FIG. 1 is a view showing the structure of the present invention

FIG. 2 is an enlarged view of the structure of the present invention

FIG. 3 is a view showing the structure of the cowling separating process of the present invention

FIG. 4 is an enlarged view of the movement of the fairing separation hinge of the present invention

FIG. 5 is a diagram of an exemplary application of the present invention

FIG. 6 is a view showing the structure of the rotary support of the present invention

FIG. 7 is a view showing the structure of the fixing support of the present invention

The structure comprises a fairing, a fairing half cover, a hinge, a fixing support, a rotating shaft, a limiting pin, a limiting groove, a bolt, a 9 nut, a 10 nut, a bolt, a 12 limiting pin mounting hole, a rotating shaft rotating hole, a rotating support fixing hole, a rotating shaft mounting hole, a 16 limiting groove and a fixing support mounting hole, wherein the fairing half cover is 1-1, the hinge is 2-3, the fixing support is 4, the rotating shaft is 5, the limiting pin is 6, the limiting groove is 7, the bolt is 8, the nut is 9, the nut is 10, the bolt is 11, the limiting pin mounting hole is 12, the rotating shaft rotating hole is 13, the rotating support fixing hole is 14, the rotating shaft mounting hole is 15, the limiting groove is 16, and the fixing support mounting hole is 17.

Detailed Description

The invention is described in detail below by way of example with reference to the accompanying drawings.

As shown in fig. 1 to 7, the invention provides a fairing rotary throwing hinge structure, which comprises a fixed support 3, a rotary support 4, a rotating shaft 5, a limiting pin 6, a limiting groove 16 and the like;

the fixed support 3 is fixedly connected to the arrow body through a bolt 11, and the rotating shaft 5 is installed on the fixed support 3 through an installation hole 15 and a nut 9 on the fixed support 3.

The rotating support 4 is fixedly connected with the half-cover 1 of the fairing through a bolt 8, the limiting pin 6 is arranged in a mounting hole 12 on the rotating support 4, and the two ends of the limiting pin 6 are fixed by nuts 10 in order to prevent the limiting pin 6 from falling off during transportation and work.

The fixed support 3 is provided with a limiting groove 16, and when the fairing is separated, the limiting pin 6 on the rotating support 4 moves in the limiting groove 16, so that the fairing half-cover 1 does not depart from the hinge rotating shaft when rotating.

When the fairing is separated, the separation force provided by the separation impulse device enables the fairing half-cover 1 to rotate outwards around the rotating shaft 5, and when the rotating angle of the fairing half-cover 1 is larger than the over-vertex angle alpha, the thrust of the carrier rocket engine acts on the rotating hole 13 of the rotating support 4, so that the rotating speed of the fairing half-cover 1 is increased. When the rotating speed of the half cowling of the fairing is increased and the centrifugal force is correspondingly increased, when the centrifugal force is increased to overcome the component of the inertia force in the opposite direction of the centrifugal force, namely after the half cowling of the fairing rotates through the unhooking angle theta, the limiting groove on the fixed support 3 stops restricting the limiting pin 6, so that the fairing is automatically separated from the hinge rotating shaft under the action of the centrifugal force, and the separation from the rocket body is completed.

Claims

1. The utility model provides a hinge structure is thrown soon to radome fairing which characterized in that: the structure comprises a fixed support 3, a rotary support 4, a rotating shaft 5, a limiting pin 6, a limiting groove 16 and the like;

the fixed support 3 is fixedly connected to the arrow body through a bolt 11; the rotating support 4 is fixedly connected with the half-cover 1 of the fairing through a bolt 8.

2. The fixing mount 3 according to claim 1, wherein: the fixed support 3 is provided with a rotating shaft mounting hole 15, and the rotating shaft 5 is mounted in the mounting hole 15 of the fixed support 3 and is fixed through a nut 9 to prevent falling off. The fixed support 3 is also provided with a limit groove 16.

3. A rotatable mount 4 as claimed in claim 1, wherein: the rotating support 4 is provided with a limit pin hole 12 and a rotating shaft rotating hole 13; the limit pin 6 is installed in the limit pin hole 12 and is prevented from falling off by nuts 10 at both ends.

4. The fairing spin-cast hinge structure as recited in claims 1, 2, and 3 further comprising: when the rotation angle of the half-cover 1 of the fairing is smaller than the over-vertex angle alpha, in order to prevent the half-cover of the fairing from separating from the rotating shaft, the limiting pin 6 on the rotating support 4 and the limiting groove 16 on the fixed support 3 are used for restricting the axial movement of the fairing.

5. The fairing spin-cast hinge structure as recited in claims 1, 2, and 3 further comprising: before the rotation angle of the half-cowling 1 of the fairing does not reach the unhooking angle theta, the rotation hole 13 on the rotating support 4 needs to ensure that the thrust of the rocket body can completely act on the rotation hole 13 of the rotating support 4.

6. The fairing spin-cast hinge structure as recited in claims 1, 2, and 3 further comprising: after the rotation angle of the half-cowling 1 passes the unhooking angle theta, the rotation hole 13 on the rotation support 4 needs to ensure that the half-cowling 1 can automatically separate from the rocket body.

7. The fairing spin-cast hinge structure as recited in claims 1, 2, and 3 further comprising: after the rotation angle of the half cowl 1 of the cowl passes the unhooking angle theta, the limit groove 16 on the fixing support 3 needs to be guaranteed to be completely separated from the limit pin 6, and the automatic separation of the half cowl 1 of the cowl is not hindered.