阅读说明：本技术 一种复材一体成型旋抛整流罩结构 (Composite material integrated into one piece throws radome fairing structure soon ) 是由 何爱颖 陈景鹏 王骏来 谢雪明 石亦琨 于 2021-08-12 设计创作，主要内容包括：本发明公开一种复材一体成型旋抛整流罩结构。整流罩结构包括端头帽、I半罩、III半罩；其中端头帽采用整体式一体成型玻璃钢结构,半罩由锥段和柱段组成,锥段、柱段采用蜂窝夹层结构,内外面板为碳纤维复合材料,芯子为芳纶纸蜂窝；在半罩的横向分离面及纵向分离面有强度加强区,加强区的材料与面板的材料一致,并通过模压与锥段、柱段一体模压成型。在横向分离面处的加强区内安装分离弹簧机构、横向爆炸螺栓盒、纵向爆炸螺栓盒、悬转铰链等结构；纵向分离面的加强区内安装爆炸螺栓盒等,并在加强区内开设相关的操作口。(The invention discloses a composite material integrally-formed rotary-polishing fairing structure. The fairing structure comprises a head cap, a half I cover and a half III cover; the end cap is of an integral integrally-formed glass fiber reinforced plastic structure, the half cover is composed of a conical section and a column section, the conical section and the column section are of a honeycomb sandwich structure, the inner panel and the outer panel are made of carbon fiber composite materials, and the core is aramid fiber paper honeycomb; the horizontal separating surface and the vertical separating surface of the half cover are provided with strength reinforcing areas, the material of the reinforcing areas is consistent with that of the panel, and the reinforcing areas, the conical section and the column section are integrally molded through mold pressing. A separation spring mechanism, a transverse explosion bolt box, a longitudinal explosion bolt box, a suspension rotation hinge and other structures are arranged in a strengthening area at the transverse separation surface; the reinforced area of the longitudinal separating surface is provided with an explosion bolt box and the like, and the reinforced area is provided with a relevant operation opening.)

1. The utility model provides a compound material integrated into one piece throws radome fairing structure soon which characterized in that: the structure comprises a head cap 1, a half cover I6, a half cover III 2, a separation spring mechanism 9, a rotating hinge 7, a transverse explosion bolt box 12, a longitudinal explosion bolt box 10 and the like.

2. The end cap of claim 1 wherein: the end cap 1 consists of an end cap shell 101 and a bottom butt joint frame 103, wherein the end cap shell 101 is made of glass fiber reinforced plastics with good heat resistance and adopts an integral structure, and the bottom butt joint frame 103 is a semicircular shell made of aluminum alloy; the end cap shell 101 is connected with the bottom butt joint frame 103 through a radial screw hole 102, the end cap 1 is connected with the III half cover 2 through an axial connecting hole 104, is in free lap joint with the I half cover 6, and seals the end cap and the I half cover veneering through rubber pads.

3. The end cap of claims 1, 2, wherein: beveling the end cap 1 along the parting surface by a certain angle theta, as shown in figure 6, so as to prevent the two half covers of the fairing from interfering when being separated; according to the flight direction of the carrier rocket, the connecting surface of the end cap and the half cover is positioned on the windward side, and the binding surface is positioned on the leeward side, so that heat flow is prevented from entering the rocket body.

4. The fairing half 2, 6 of claim 1 wherein: the I half cover 6 and the III half cover 2 are composed of a conical section 3 and a column section 4, the conical section 3 and the column section 4 adopt honeycomb sandwich structures, the inner panel 203 and the outer panel 203 are made of carbon fiber composite materials, and the honeycomb core 204 is made of aramid paper honeycomb; a reinforcing piece 205 is embedded at the connecting part of the conical section 3 and the column section 4, and the conical section 3 and the column section 4 are integrally formed through mould pressing.

5. The fairing half 2, 6 of claim 1, 3 wherein: the transverse separating surface of the half cover I6 and the half cover III 2 is provided with a reinforcing area, the material of the reinforcing area is consistent with that of the panel, and the reinforcing area, the conical section and the column section are integrally formed through mould pressing.

6. The fairing half 2, 6 of claim 1, 3, 4 wherein: the longitudinal separation surface of the half cover I6 and the half cover III 2 is provided with a reinforced area, the material of the reinforced area is consistent with that of the panel, and the reinforced area, the conical section and the column section are integrally formed through mould pressing.

7. The fairing half 2, 6 of claim 1, 3, 4 wherein: the I half cover 6 and the III half cover 2 are transversely butted with each other, and the half covers are integrally molded; the longitudinal butt frames 206 of the half cover I6 and the half cover III 2 are molded separately and riveted on the half covers through rivets.

8. The fairing half 2, 6 of claim 1, 4, 5 wherein: explosion bolt operation ports 8 and 13 are formed in the reinforced area of the half cover, and a transverse explosion bolt box 12 and a longitudinal explosion bolt box 10 are riveted at the operation ports of the reinforced area of the half cover.

9. The fairing half 2, 6 of claim 1, 4 wherein: the separation spring mechanism 9 and the rotary hinge 7 are riveted on the half cover reinforcing area 201 through rivets.

10. The fairing as recited in claim 1, wherein: after the fairing is installed, the operation opening on the half-cover is sealed through the opening cover; according to the specific use requirement of the carrier rocket load, an air conditioning port and an exhaust hole can be formed in the half cover; the fairing as recited in claim 1, wherein: the inside of the fairing is provided with measuring instruments such as an inertial measurement unit, a remote measurement unit and the like, and a wave transmission port can be formed at the position corresponding to the fairing.

Technical Field

The invention belongs to the technical field of carrier rockets and the like, and particularly relates to a composite material integrally formed rotary-throwing fairing structure.

Background

The fairing is arranged at the head of the carrier rocket, and the lower end of the fairing is connected with other cabin sections of the rocket body. The main functions are as follows: firstly, the carrier rocket has a better aerodynamic shape in flight, and the aerodynamic resistance of flight is reduced; secondly, the effective load such as the satellite is protected from the influence of pneumatic heating and aerodynamic force when flying through the atmosphere. When the carrier rocket passes through the atmosphere, the protective effect of the fairing is finished, and the fairing needs to be separated from the carrier rocket and thrown away, so that the structural mass of the rocket is reduced, and the carrying capacity is improved.

At present, the fairing of the carrier rocket generally adopts a separation mode of spin-throwing, namely, the fairing is divided into two half-shrouds, the two half-shrouds are transversely and longitudinally connected through an explosive bolt, and a rotary hinge is designed on the half-shrouds and the rocket body. When the separating instruction is sent out, the transverse and longitudinal explosion bolts are unlocked, the separating spring provides separating force, the two half covers rotate around the respective hinge rotating shafts, and the separation of the fairing and the arrow body is completed. The fairing adopting the separation mode has the characteristics of simple structure, low cost, high reliability, mature technology and the like.

The common spin-casting fairing is in a structural form combining a semi-hard shell structure and a honeycomb sandwich structure, the semi-hard shell structure is adopted at the part with large axial pressure and small external pressure, and the honeycomb sandwich structure is adopted at the part with small axial pressure and large external pressure. The connecting part of the fairing and the arrow body adopts a semi-hard shell structure, the front end of the fairing adopts a honeycomb sandwich structure, and the structural form can bear large axial pressure and has high structural efficiency. Because the monocoque structure generally adopts the grid of metal to add muscle or the skin purlin structural style, need be connected with honeycomb sandwich structure section after the processing is accomplished, increased the complexity of design, processing, assembly.

Disclosure of Invention

In view of the above, the invention provides a composite material integrally formed spin-cast fairing structure, which can bear a large combined action force of axial pressure and external pressure and can bear concentrated loads on transverse separation points, and has the advantages of small mass, high structural efficiency, simple design and processing, short processing period, low cost, reliable separation and the like.

A composite material integrated rotary-throwing fairing structure comprises a head cap, a half I cover, a half III cover and the like; the two half covers are symmetrical about the quadrant line II-IV, and the half cover I and the half cover III are connected through a longitudinal explosion bolt. A separation spring is installed near the transverse separation plane, and hinges are installed near the I-quadrant line and the III-quadrant line. When the fairing is separated, the transverse and longitudinal explosion bolts are exploded, and the two half shrouds rotate around the hinge rotating shaft to be separated under the action of the separation spring, so that the fairing is separated from the rocket body.

The end cap is made of glass fiber reinforced plastics with good heat resistance and adopts an integral structure, and the bottom of the end cap is provided with a butt joint frame through a radial screw; in order to prevent the two half covers of the fairing from colliding during separation, the end cap edges are obliquely cut at a certain angle along the separation surface.

The I half cover and the III half cover are composed of a conical section and a column section, the conical section and the column section adopt honeycomb sandwich structures, the inner panel and the outer panel are made of carbon fiber composite materials, and the core is aramid fiber paper honeycomb; and a reinforcing part is embedded in the connecting part of the conical section and the column section, so that the rigidity and strength change of the transition section caused by stress concentration is increased. The transverse separating surface and the longitudinal separating surface of the half cover I and the half cover III are provided with strength reinforcing areas, the materials of the strength reinforcing areas are consistent with those of the panel, and the strength reinforcing areas, the conical section and the column section are integrally formed through mould pressing.

A separating spring mechanism, a rotating hinge, an explosion bolt box, a rotating throwing hinge and other structural components are arranged in the transverse separating surface reinforcing area, and windows such as a separating spring operation port, an air conditioning port, an exhaust hole and the like are arranged; and an explosive bolt box is arranged in the reinforcing area of the longitudinal separation surface, and an explosive bolt operation port and the like are formed in the explosive bolt box. After the fairing is installed, the operation opening is sealed through the opening cover.

Drawings

FIG. 1 is a structural view and a sectional view of the present invention

FIG. 2 is a partial enlarged view I of the junction between the cone section and the column section according to the present invention

FIG. 3 is a partial enlarged view II of the junction between the column segment and the reinforcement region according to the present invention

FIG. 4 is an enlarged view of a portion of the longitudinal separation plane reinforcing region III according to the present invention

FIG. 5 is a partial enlarged view of the joint between the end cap and the half cover I according to the present invention

FIG. 6 is a schematic view of an end cap of the present invention

FIG. 7 is a view showing the structure of a transverse explosion bolt case

FIG. 8 is a view showing the structure of a longitudinal explosion bolt case

Wherein, 1-end cap, 2-III half cover, 3-taper section, 4-column section, 5-explosive bolt operation port, 6-I half cover, 7-rotary hinge, 8-separation spring operation port, 9-separation spring mechanism, 10-longitudinal explosive bolt box, 11-exhaust hole, 12-transverse explosive bolt box, 13-explosive bolt operation port;

101-end cap shell, 102-end cap shell and butt-joint frame connecting hole, 103-end cap bottom butt-joint frame, 104-end cap and I half cover connecting hole;

201-III half-cover column section transverse separation surface reinforcing region, 202-III half-cover column section longitudinal separation surface reinforcing region, 203-inner and outer panels, 204-honeycomb core, 205-cone and column transition reinforcing member, 206-two half-cover longitudinal butt-joint frame;

Detailed Description

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

As shown in fig. 1 and 2, the invention provides a composite material integrally formed spin-cast fairing structure, which comprises a head cap 1, a half I cover 6, a half III cover 2, a separating spring mechanism 9, a rotating hinge 7, a transverse explosion bolt box 12, a longitudinal explosion bolt box 10 and the like.

The end cap 1 consists of an end cap shell 101 and a bottom butt joint frame 103, wherein the end cap shell 101 is made of glass fiber reinforced plastics with good heat resistance and adopts an integral structure, and the bottom butt joint frame 103 is a semicircular shell made of aluminum alloy; the end cap shell 101 is connected with a bottom butt joint frame 103 through a radial screw hole 102, the end cap 1 is connected with the III half cover 2 through an axial connecting hole 104, is in free lap joint with the I half cover 6, seals an abutting surface of the end cap and the I half cover through a rubber pad, and when the fairing is separated, the end cap 1 is separated from the arrow body and the I half cover 6 along with the III half cover 2.

According to the flight direction of the carrier rocket, the connecting surface of the end cap 1 and the half cover is positioned on the windward side, and the binding surface is positioned on the leeward side, so that heat flow is prevented from entering the rocket body.

The end cap 1 is chamfered along the parting plane by a certain angle theta as shown in figure 6, so as to prevent the two half cowls of the fairing from interfering when being separated.

The I half cover 6 and the III half cover 2 are composed of a conical section 3 and a column section 4, the conical section 3 and the column section 4 adopt honeycomb sandwich structures, the inner panel 203 and the outer panel 203 are made of carbon fiber composite materials, and the honeycomb core 204 is made of aramid paper honeycomb; a reinforcing piece 205 is embedded at the connecting part of the conical section 3 and the column section 4, and the conical section 3 and the column section 4 are integrally formed through mould pressing.

The transverse separating surface of the I half cover 6 and the III half cover 2 has higher requirement on the structural strength of the fairing due to bearing concentrated load and arranging an operation port, the honeycomb sandwich structure cannot bear larger axial force and concentrated load, a reinforcing area is arranged at the transverse separating surface, the material of the reinforcing area is consistent with that of the panel, and the reinforcing area and the column section are integrally formed through mould pressing.

The longitudinal separation surfaces of the half cover I6 and the half cover III 2 bear concentrated load and are provided with operation ports, the longitudinal separation surfaces are provided with reinforced areas, the materials of the reinforced areas are consistent with those of the panel, and the reinforced areas, the cone section and the column section are integrally formed through mould pressing.

The transverse butt-joint frames of the half cover I6 and the half cover III 2 and the half cover are integrally molded, and in order to ensure simple process and low cost of the half cover molding, the longitudinal butt-joint frames 206 of the half cover I6 and the half cover III 2 are separately molded and riveted on the half cover through rivets.

The reinforced area is provided with explosive bolt operation ports 8 and 13, and a transverse explosive bolt box 12 and a longitudinal explosive bolt box 10 are riveted at the operation port of the semi-cover reinforced area, so that the explosive bolts can be conveniently connected, and the operation ports are sealed through the opening covers after the explosive bolts are connected.

Separation spring mechanism 9, swivel hinge 7 pass through rivet riveting in partly covering reinforcing area 201, for making radome fairing and arrow body convenient assembling, the separation spring is the locking state before radome fairing and arrow body assembly, and after radome fairing and arrow body butt joint, need release the elasticity of spring, make it act on the arrow body, set up spring operation mouth in the position that partly covers correspondence, make things convenient for the unblock of spring, after the spring unblock, seal the operation mouth through the flap.

According to the specific use requirement of the carrier rocket load, an air conditioning port and an exhaust hole can be arranged in the reinforced area of the half cover.

For example, the inside of the fairing is provided with measuring instruments such as an inertial measurement unit, a remote measurement unit and the like, and a wave-transmitting port can be arranged at the position corresponding to the fairing.