阅读说明：本技术 一种在同一弹体截面安装的多组独立舵面和尾翼合件装置 (Multi-group independent control surface and tail wing assembly device installed on same projectile body section ) 是由 曹玉鑫 郭沫然 于 2021-07-28 设计创作，主要内容包括：本发明公开了一种在同一弹体截面安装的多组独立舵面和尾翼合件装置,该装置包括组合本体、多个舵面合件、和多个尾翼合件；组合本体包括固定块、夹持块一、和夹持块二,夹持块一位于固定块和夹持块二之间,夹持块一和夹持块二的相对面均分别开设有多个半孔一和多个半孔二,多个半孔一和多个半孔二沿周向间隔交错布置；夹持块一的半孔一与夹持块二的半孔一一一对应,且对应的两个半孔一合成一个完整的轴承孔,轴承孔与轴承配合；夹持块一的半孔二与夹持块二的半孔二一一对应,且对应的两个半孔二合成一个完整的轴孔,轴孔与翼转轴二配合；固定块连接有多个电机,每个电机的输出轴均设有与锥齿轮一啮合的锥齿轮二。(The invention discloses a device for assembling a plurality of groups of independent control surfaces and tail wings on the same missile body, which comprises a combined body, a plurality of control surface assemblies and a plurality of tail wing assemblies; the combined body comprises a fixed block, a first clamping block and a second clamping block, wherein the first clamping block is positioned between the fixed block and the second clamping block, a plurality of first half holes and a plurality of second half holes are respectively formed in opposite surfaces of the first clamping block and the second clamping block, and the first half holes and the second half holes are arranged at intervals in a staggered mode along the circumferential direction; the half holes I of the first clamping block correspond to the half holes I of the second clamping block one by one, the two corresponding half holes I are combined into a complete bearing hole, and the bearing hole is matched with a bearing; the half holes II of the first clamping block correspond to the half holes II of the second clamping block one to one, the two corresponding half holes II are combined into a complete shaft hole, and the shaft hole is matched with the wing rotating shaft II; the fixed block is connected with a plurality of motors, and the output shaft of each motor is provided with a bevel gear II meshed with the bevel gear I.)

1. The utility model provides an independent rudder face of multiunit and fin closes piece device at same projectile body cross-section installation which characterized in that: the combined rudder comprises a combined body, a plurality of control surface assemblies and a plurality of tail wing assemblies; the control surface assemblies and the tail wing assemblies are arranged in a staggered mode at intervals along the circumferential direction of the combined body; each said control surface assembly comprising: the device comprises a first wing rotating shaft, a first control surface rotationally connected to one end of the first wing rotating shaft, a bearing sleeved at the other end of the first wing rotating shaft, a first bevel gear sleeved outside the first wing rotating shaft, and a first driving assembly driving the first control surface to expand, wherein the first bevel gear is positioned between the first control surface and the bearing; each of the tail assemblies comprising: the wing rotating shaft II, a control surface II which is rotatably connected to one end of the wing rotating shaft II and a driving assembly II which drives the control surface II to unfold;

the combined body comprises a fixed block, a first clamping block and a second clamping block, wherein the first clamping block is positioned between the fixed block and the second clamping block, a plurality of first half holes and a plurality of second half holes are respectively formed in opposite surfaces of the first clamping block and the second clamping block, and the first half holes and the second half holes are arranged at intervals in a staggered mode along the circumferential direction; the half holes I of the first clamping block correspond to the half holes I of the second clamping block one by one, the two corresponding half holes I form a complete bearing hole, and the bearing hole is matched with the bearing; the half holes II of the first clamping block correspond to the half holes II of the second clamping block one to one, the two corresponding half holes II are combined into a complete shaft hole, and the shaft hole is matched with the wing rotating shaft II; the fixed block is connected with a plurality of motors, and an output shaft of each motor is provided with a bevel gear II meshed with the bevel gear I.

2. The multiple independent sets of control surface and tail assembly devices mounted on the same projectile section as in claim 1, wherein: mounting grooves are formed in the ends, far away from the combined body, of the first wing rotating shaft and the second wing rotating shaft; a rotating shaft is connected between two opposite side walls of the mounting groove; one end of the first control surface is positioned in the mounting groove of the first wing rotating shaft and sleeved outside the rotating shaft; one end of the second control surface is located in the mounting groove of the second wing rotating shaft and is sleeved outside the rotating shaft.

3. The multiple independent sets of control surface and tail assembly devices mounted on the same elastomeric section of claim 2, wherein: one ends of the first control surface and the second control surface, which are positioned in the mounting grooves, are both in threaded connection with adjusting screws; the adjusting screw is used for adjusting the unfolding angle of the first control surface and the second control surface.

4. The multiple independent sets of rudder and tail assemblies mounted on the same elastomeric section as in any one of claims 1 to 3 wherein: the first driving assembly and the second driving assembly both comprise: a compression spring and a limiting block; mounting holes in sliding fit with the limiting blocks are formed in the ends, far away from the combined body, of the first wing rotating shaft and the second wing rotating shaft; two ends of the compression spring respectively abut against the hole bottom of the mounting hole and the limiting block; when the first control surface or the second control surface is in a folded state, the end part of the limiting block abuts against the first control surface or the second control surface; when the first control surface or the second control surface is in an unfolded state, the peripheral wall of the limiting block abuts against the first control surface or the second control surface so as to lock an unfolded angle.

5. The multiple independent sets of control surface and tail assembly devices installed on the same missile body section as in claims 1 to 3 are characterized in that: one end of the first wing rotating shaft, which is far away from the first control surface, is in threaded connection with an adjusting nut; the bearing is positioned between the adjusting nut and the first control surface; the adjusting nut is used for adjusting the radial position of the first wing rotating shaft, so that the meshing backlash of the first bevel gear and the second bevel gear is zero.

6. The multiple independent sets of control surface and tail assembly devices installed on the same missile body section as in claims 1 to 3 are characterized in that: at least one of the first clamping block and the second clamping block is annular; a pin is inserted into one end of the wing rotating shaft II, which is far away from the control surface II; the pin is located within the annular interior.

7. The multiple independent sets of control surface and tail assembly devices installed on the same missile body section as in claims 1 to 3 are characterized in that: two ends of the first half hole are convexly provided with limiting bulges; the bearing is positioned between the two limiting bulges.

Technical Field

The invention belongs to the technical field of projectile servo mechanisms, and particularly relates to a plurality of groups of independent control surface and empennage assembly devices which are arranged on the same projectile section.

Background

At present, small-sized missiles at home and abroad are provided with various forms of servo mechanisms and empennage mechanisms, but the servo mechanisms and the empennage mechanisms are not on the same cross section of a missile body. The drawbacks of this structure are: the control surface mechanism and the tail wing mechanism are respectively arranged on different projectile body sections, and occupy one section of projectile body, so that the occupied space is large, the structure is complex, and the types of parts are various.

Disclosure of Invention

The invention aims to provide a device for mounting a plurality of groups of independent control surfaces and tail wing assemblies on the same missile body section, so as to solve the problem that the independent deflectable control surface assemblies and the non-deflectable tail wing assemblies are mounted on the same section on a missile body.

The technical scheme adopted by the invention is as follows:

the independent control surface and tail wing assembly devices are arranged on the same missile body section and comprise a combined body, a plurality of control surface assemblies and a plurality of tail wing assemblies; the control surface assemblies and the tail wing assemblies are arranged in a staggered mode at intervals along the circumferential direction of the combined body; each said control surface assembly comprising: the device comprises a first wing rotating shaft, a first control surface rotationally connected to one end of the first wing rotating shaft, a bearing sleeved at the other end of the first wing rotating shaft, a first bevel gear sleeved outside the first wing rotating shaft, and a first driving assembly driving the first control surface to expand, wherein the first bevel gear is positioned between the first control surface and the bearing; each of the tail assemblies comprising: the wing rotating shaft II, a control surface II which is rotatably connected to one end of the wing rotating shaft II and a driving assembly II which drives the control surface II to unfold;

the combined body comprises a fixed block, a first clamping block and a second clamping block, wherein the first clamping block is positioned between the fixed block and the second clamping block, a plurality of first half holes and a plurality of second half holes are respectively formed in opposite surfaces of the first clamping block and the second clamping block, and the first half holes and the second half holes are arranged at intervals in a staggered mode along the circumferential direction; the half holes I of the first clamping block correspond to the half holes I of the second clamping block one by one, the two corresponding half holes I form a complete bearing hole, and the bearing hole is matched with the bearing; the half holes II of the first clamping block correspond to the half holes II of the second clamping block one to one, the two corresponding half holes II are combined into a complete shaft hole, and the shaft hole is matched with the wing rotating shaft II; the fixed block is connected with a plurality of motors, and an output shaft of each motor is provided with a bevel gear II meshed with the bevel gear I.

As a further alternative of the device with multiple groups of independent control surfaces and tail wing assemblies arranged on the same projectile body section, mounting grooves are formed in the ends, far away from the combined body, of the first wing rotating shaft and the second wing rotating shaft; a rotating shaft is connected between two opposite side walls of the mounting groove; one end of the first control surface is positioned in the mounting groove of the first wing rotating shaft and sleeved outside the rotating shaft; one end of the second control surface is located in the mounting groove of the second wing rotating shaft and is sleeved outside the rotating shaft.

As a further alternative of the device with a plurality of groups of independent control surfaces and tail wing assemblies arranged on the same missile body section, one ends of the first control surface and the second control surface, which are positioned in the installation grooves, are both in threaded connection with adjusting screws; the adjusting screw is used for adjusting the unfolding angle of the first control surface and the second control surface.

As a further alternative to the arrangement of separate sets of control surfaces and tail assemblies mounted on the same section of a projectile, the first and second drive assemblies each comprise: a compression spring and a limiting block; mounting holes in sliding fit with the limiting blocks are formed in the ends, far away from the combined body, of the first wing rotating shaft and the second wing rotating shaft; two ends of the compression spring respectively abut against the hole bottom of the mounting hole and the limiting block; when the first control surface or the second control surface is in a folded state, the end part of the limiting block abuts against the first control surface or the second control surface; when the first control surface or the second control surface is in an unfolded state, the peripheral wall of the limiting block abuts against the first control surface or the second control surface so as to lock an unfolded angle.

As a further alternative of the device for installing a plurality of groups of independent control surfaces and tail assemblies on the same missile body section, one end of the first wing rotating shaft, far away from the first control surface, is in threaded connection with an adjusting nut; the bearing is positioned between the adjusting nut and the first control surface; the adjusting nut is used for adjusting the radial position of the first wing rotating shaft, so that the meshing backlash of the first bevel gear and the second bevel gear is zero.

As a further alternative to the arrangement of multiple sets of independent control surfaces and tail assemblies mounted on the same projectile section, at least one of the first and second clamping blocks is annular; a pin is inserted into one end of the wing rotating shaft II, which is far away from the control surface II; the pin is located within the annular interior.

As a further alternative of the device of the plurality of groups of independent control surfaces and tail wing assemblies arranged on the same projectile body section, two ends of the half hole I are convexly provided with limiting bulges; the bearing is positioned between the two limiting bulges.

The invention has the beneficial effects that: the motor is fixed through the fixing plate, the control surface assembly and the tail wing assembly are fixed through the first clamping plate and the second clamping plate, the tail wing assembly of the control surface assembly is located on the same cross section of the projectile body, the structure is simple, the cost is low, and the direction of development of the small-caliber projectile body steering engine and the tail wing is represented.

Drawings

FIG. 1 is a schematic structural diagram of multiple independent sets of control surface and tail assembly devices mounted on the same projectile section according to the present invention.

Fig. 2 is a schematic view of the structure of the combined body of the multiple independent sets of control surfaces and tail assemblies installed in the same projectile section as shown in fig. 1.

Fig. 3 is a schematic view of the arrangement of control surfaces in the same set of separate control surface and tail assembly devices shown in fig. 1 installed in the same missile section.

Fig. 4 is a schematic view of the structure of the tail assembly of fig. 1 in the arrangement of multiple independent control surfaces and tail assemblies mounted in the same projectile section.

FIG. 5 is a schematic illustration of the installation of control surface assemblies in multiple independent sets of control surface and tail assembly arrangements shown in FIG. 1 installed in the same missile section.

In the figure: 1-a composite body; 2, a motor; 3-control surface assembly; 4-a tail assembly; 5, fixing a plate; 6, clamping a first plate; 7-clamping a second plate; 8-wing rotating shaft I; 9-a rotating shaft; 10-a rudder surface; 11-a limiting block; 12-a compression spring; 13-adjusting screws; 14-a bearing; 15-adjusting the nut; 16-bevel gear one; 17-a pin; 18-wing rotating shaft II; 19-half hole one; 20-half hole II; 21-tail fin; .

Detailed Description

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the present invention will be briefly described below with reference to the accompanying drawings and the embodiments or the description in the prior art, it is obvious that the following description of the structure of the drawings is only some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.

The technical solution provided by the present invention will be described in detail by way of embodiments with reference to the accompanying drawings. It should be noted that the description of the embodiments is provided to help understanding of the present invention, but the present invention is not limited thereto.

In some instances, some embodiments are not described or not in detail, as they are conventional or customary in the art.

Furthermore, the technical features described herein, or the steps of all methods or processes disclosed, may be combined in any suitable manner in one or more embodiments, in addition to the mutually exclusive features and/or steps. It will be readily appreciated by those of skill in the art that the order of the steps or operations of the methods associated with the embodiments provided herein may be varied. Any order in the drawings and examples is for illustrative purposes only and does not imply that a certain order is required unless explicitly stated to be required.

The numbering of the components as such, e.g., "first", "second", etc., is used herein only to distinguish the objects as described, and does not have any sequential or technical meaning. The terms "connected" and "coupled" when used in this application, encompass both direct and indirect connections (and couplings) where appropriate and where not necessary contradictory.

As shown in fig. 1 to 5, the multiple independent control surface and tail assembly devices installed on the same missile body section of the present embodiment include a combined body 1, multiple control surface assemblies 3, and multiple tail assemblies 4; the control surface assemblies 3 and the tail wing assemblies 4 are arranged in a staggered mode at intervals along the circumferential direction of the combined body 1; each control surface arrangement 3 comprises: the device comprises a wing rotating shaft I8, a control surface I10 rotationally connected to one end of the wing rotating shaft I8, a bearing 14 sleeved at the other end of the wing rotating shaft I8, a bevel gear I16 sleeved outside the wing rotating shaft I8 and a driving assembly I for driving the control surface I10 to unfold, wherein the bevel gear I16 is positioned between the control surface I10 and the bearing 14; each tail assembly 4 comprises: the wing rotating shaft II 18, the tail 21 rotatably connected to one end of the wing rotating shaft II 18 and the driving assembly II for driving the tail 21 to unfold;

the combined body 1 comprises a fixed block, a first clamping block and a second clamping block, wherein the first clamping block is positioned between the fixed block and the second clamping block, a plurality of first half holes 19 and a plurality of second half holes 20 are respectively formed in opposite surfaces of the first clamping block and the second clamping block, and the first half holes 19 and the second half holes 20 are arranged in a staggered mode at intervals along the circumferential direction; the half holes I19 of the first clamping block I correspond to the half holes I19 of the second clamping block I one by one, the two corresponding half holes I19 are combined into a complete bearing hole, and the bearing hole is matched with the bearing 14; the half-hole II 20 of the first clamping block corresponds to the half-hole II 20 of the second clamping block one by one, the two corresponding half-hole II 20 are combined into a complete shaft hole, and the shaft hole is matched with the wing rotating shaft II 18; the fixed block is connected with a plurality of motors 2, and the output shaft of each motor 2 is provided with a bevel gear II meshed with the bevel gear I16.

The number of the control surface assemblies 3 and the number of the tail assemblies 4 are determined according to actual needs, in the embodiment, four groups of control surface assemblies 3 and four groups of tail assemblies 4 are respectively arranged, the four groups of control surface assemblies 3 and the four groups of tail assemblies 4 are uniformly arranged on the same projectile body section, and specifically, the four groups of control surface assemblies 3 and the four groups of tail assemblies 4 are arranged between a first clamping block and a second clamping block; four bearings 14 of the four groups of control surface assemblies 3 are arranged in the four bearing holes; four wing rotating shafts 18 of the four tail assemblies 4 are arranged in the four shaft holes; during installation, the first clamping block and the second clamping block are separated, the four bearings 14 are respectively placed in the first clamping block or the first four half holes 19 of the second clamping block, the second four wing rotating shafts 18 are respectively placed in the first clamping block or the second four half holes 20 of the second clamping block, then the first clamping block and the second clamping block are closed, the first clamping block and the second clamping block are detachably fixed, and then the fixing plate 5 provided with the four motors 2 is detachably fixed to the first clamping block. Thereby realizing that a plurality of control surface assemblies 3 and a plurality of tail wing assemblies 4 are arranged on the same cross section of the projectile body.

In one embodiment, mounting grooves are formed in both ends of the first wing rotating shaft 8 and the second wing rotating shaft 18, which are far away from the combined body 1; a rotating shaft 9 is connected between two opposite side walls of the mounting groove; one end of the first control surface 10 is positioned in the mounting groove of the first wing rotating shaft 8 and is sleeved outside the rotating shaft 9; one end of the tail wing 21 is positioned in the mounting groove of the wing rotating shaft II 18 and is sleeved outside the rotating shaft 9. One of the two opposite side walls of the mounting groove can be provided with a hole matched with the rotating shaft 9, and the other side wall of the mounting groove is provided with a threaded hole in threaded connection with the rotating shaft 9, so that one end of the rotating shaft 9 sequentially penetrates through the first wing rotating shaft 8, the second wing rotating shaft 18 and the hole in the side wall of the mounting groove, and the other end of the rotating shaft 9 is in threaded connection with the threaded hole in the other side wall of the mounting groove; it is obvious that other ways of fixing the shaft 9 are also possible. The rotation axis of the first control surface 10 is perpendicular to the extending direction of the first wing rotating shaft 8, the first control surface 10 rotates around the rotating shaft 9 under the driving of the first driving assembly, so that the first control surface is unfolded, and after the first control surface is unfolded, the motor 2 receives instructions and drives the first control surface 10 to rotate around the extending direction of the first wing rotating shaft 8 through the first bevel gear 16 and the second bevel gear, and therefore yawing, pitching and rotation stopping of the projectile body are achieved. The tail wing 21 rotates around the rotating shaft 9 under the driving of the driving assembly II, so that the tail wing 21 is unfolded to provide lifting force for the projectile body and keep the projectile body stably flying.

In one embodiment, an adjusting screw 13 is connected with one end of the first control surface 10 and one end of the tail wing 21 in the installation groove in a threaded mode; the adjusting screw 13 is used for adjusting the unfolding angle of the control surface-10 and the tail 21. Adjusting screw 13 is located the pivot 9 and is close to one side of combination body 1, and bevel gear 16 is opened has the groove of dodging control surface one 10, rotates adjusting screw 13, and the distance that adjusting screw 13 stretches out control surface one 10 changes, and adjusting screw 13 supports to wing pivot 8 back, and control surface one 10 no longer rotates to reach the expansion angle of adjusting control surface one 10.

In one embodiment, the first and second drive assemblies each comprise: a compression spring 12 and a stopper 11; mounting holes in sliding fit with the limiting blocks 11 are formed in the ends, far away from the combined body 1, of the first wing rotating shaft 8 and the second wing rotating shaft 18; two ends of the compression spring 12 respectively abut against the hole bottom of the mounting hole and the limiting block 11; when the first control surface 10 or the empennage 21 is in a folded state, the end part of the limiting block 11 is abutted against the first control surface 10 or the empennage 21; when the first control surface 10 or the empennage 21 is in the unfolding state, the peripheral wall of the limiting block 11 is abutted against the first control surface 10 or the empennage 21 so as to lock the unfolding angle.

When the projectile body is stored, namely the projectile body is positioned in the projectile barrel, the compression springs 12 in the first wing rotating shaft 8 and the second wing rotating shaft 18 are compressed, and the first control surface 10 or the tail wing 21 is folded; when the projectile body is launched, the projectile body leaves the projectile barrel, the compression spring 12 pushes the first control surface 10 and the first tail wing 21 to rotate around the rotating shaft 9, when the adjusting screw 13 touches the first wing rotating shaft 8 and the second wing rotating shaft 18, the first control surface 10 and the first tail wing 21 are unfolded in place, at the moment, the first control surface 10 and the first tail wing 21 are limited by the limiting block 11 below the first control surface 10 and the second tail wing 21, the first tail wing 10 cannot retract, and the unfolding angle is locked.

In one embodiment, an end of the wing rotating shaft I8 far away from the control surface I10 is in threaded connection with an adjusting nut 15; the bearing 14 is positioned between the adjusting nut 15 and the first control surface 10; the adjusting nut 15 is used for adjusting the radial position of the wing rotating shaft I8, so that the meshing backlash of the bevel gear I16 and the bevel gear II is zero, and the deflection angle of the control surface I10 can be adjusted more accurately.

In one embodiment, at least one of the first clamping block and the second clamping block is annular; a pin 17 is inserted into one end of the wing rotating shaft II 18 far away from the tail wing 21; the pins 17 are located within the ring so that the tail assembly 4 is held in a zero position by the pins 17.

In one embodiment, both ends of the first half-hole 19 are convexly provided with limiting bulges; the bearing 14 is located between the two stop lugs.

The invention is not limited to the above alternative embodiments, and any other various forms of products can be obtained by anyone in the light of the present invention, but any changes in shape or structure thereof, which fall within the scope of the present invention as defined in the claims, fall within the scope of the present invention.