Small low-cost three-channel steering engine room mechanism

Abstract

The invention provides a small low-cost three-channel steering engine room mechanism. The steering engine room mechanism comprises a first steering engine room assembly, a gear transmission assembly, a second steering engine room assembly and a rudder piece. The first steering engine room assembly, the gear transmission assembly and the second steering engine room assembly are arranged in a stacked mode from top to bottom, the whole steering engine room mechanism is cylindrical, and the first steering engine room assembly, the gear transmission assembly and the second steering engine room assembly are sequentially arranged from top to bottom. Four rudder sheets which are arranged in a cross shape are uniformly distributed on the periphery of the steering engine room mechanism; the first steering engine room assembly and the second steering engine room assembly are the same in structure. The first steering engine room assembly, the gear transmission assembly and the second steering engine room assembly are fixedly connected through circumferential screws. The rudder sheets are circumferentially and annularly distributed along the outer contour of the middle base assembly and fixedly connected with the exposed rudder sheet shaft installation position on the middle base assembly through screws near the wing root.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of guided rocket control, in particular to a small and low-cost three-channel rudder cabin mechanism. BACKGROUND

[0002] With the increasingly obvious characteristics of unmanned and informatization of modern war, a large number of aircrafts with the basic characteristics of low flight altitude, slow flight speed and small size appear on the battlefield. Specifically, there are cruise missiles, kamikaze UAVs, first-person view UAVs (FPV) and the like.

[0003] The above new quality combat forces have the characteristics of low cost, slow flight speed and small size, which are in sharp contrast to the traditional air defense system which targets high-value, high flight speed and flexible manned aircraft, and also pose new challenges to the traditional air defense system.

[0004] The traditional machine gun air defense has low hit rate and is not capable of facing the enemy UAV swarm attack; and although the directional energy weapons such as microwave weapons and laser weapons have high efficiency and cost ratio, they are not mature in technology, have limited striking range and poor mobility; the strategy of using "machine against machine" and "swarm against swarm" for countermeasures will face the shortcomings of complex control system, low interception speed and slow reaction speed.

[0005] The traditional missile air defense system has less spare ammunition and high price, and it is difficult to achieve a good efficiency and cost ratio when facing low, slow and small targets. Since it targets high flight performance targets, the rudder control mechanism is complex, and a custom rudder is often used, which occupies a large volume of the missile body. When designing, the size of the missile body must be increased to ensure the installation space of the rudder and related mechanisms. Moreover, it is subjected to a large overload, the components are required to be high, and the cost is high, which is difficult to realize miniaturization.

[0006] Therefore, in order to intercept cruise missiles and other low, slow and small targets, it is necessary to develop a rocket weapon that can achieve considerable precision by using a command guidance system to achieve precise hard kill on enemy targets, and can also achieve the basic combat requirements of high yield, fast reaction and low cost. That is, a command guided rocket for low-altitude target interception is designed. SUMMARY

[0007] The present application provides a small and low-cost three-channel rudder cabin mechanism to solve the problem of large volume of the missile body in the prior art.

[0008] The present application provides a small and low-cost three-channel rudder cabin mechanism, which comprises:

[0009] a rudder cabin assembly A, a gear transmission assembly, a rudder cabin assembly B and a rudder blade;

[0010] The rudder cabin assembly A, the gear transmission assembly and the rudder cabin assembly B are arranged in a stacking manner from top to bottom,

[0011] The rudder cabin mechanism is in a cylindrical shape, and is sequentially arranged from top to bottom in the order of the rudder cabin assembly A, the gear transmission assembly and the rudder cabin assembly B; four rudder blades arranged in a cross shape are uniformly distributed around the rudder cabin mechanism;

[0012] The rudder cabin assembly A and the rudder cabin assembly B are in a central symmetrical relationship; the rudder cabin assembly A, the gear transmission assembly and the rudder cabin assembly B are fixedly connected through circumferential screws; the rudder blades are circumferentially arranged around the outer contour of the middle base assembly and are fixedly connected to the exposed rudder blade shaft mounting positions on the middle base assembly through screws near the wing roots.

[0013] Further, the rudder cabin assembly A and the rudder cabin assembly B are respectively inserted into the upper and lower ends of the gear transmission assembly;

[0014] The upper end of the rudder cabin assembly A and the rudder cabin assembly B is circumferentially uniformly provided with four threaded holes, and the lower end is circumferentially uniformly provided with two threaded holes; the upper and lower ends of the gear transmission assembly are provided with countersunk holes, and the cabin sections are fixedly connected through circumferential screws.

[0015] Further, the rudder cabin assembly A includes a rudder housing A, a finished servo motor and a drive gear;

[0016] The drive gear is connected to the finished servo motor through a screw;

[0017] The finished servo motors are arranged in a staggered manner and are centrally symmetrically placed in the preset mounting groove of the rudder housing A, and are fixed by mounting the gear transmission assembly.

[0018] Further, the rudder housing A is provided with through holes around the periphery, threaded holes for mounting a circuit control board on the back, four threaded holes uniformly distributed around the upper end, and two threaded holes uniformly distributed around the lower end; the front end is used for fixed connection after being plugged with the base, and the rear end is a hole position for connecting with other components of the missile.

[0019] Further, the rudder cabin assembly B is in a cylindrical shape and includes:

[0020] A finished servo motor, a drive gear and a rudder housing B; the assembly relationship of the finished servo motor, the drive gear and the rudder housing B is the same as that of the rudder cabin assembly A.

[0021] Further, the middle base is in a cylindrical shape, and is divided into four symmetrical quadrants in space;

[0022] Each quadrant has two shaft mounting hole positions; the two shaft mounting hole positions are different in size;

[0023] The large mounting hole is located in the middle of the whole middle base; the small mounting hole is located according to the position of the finished motor and the size of the gear and is arranged beside the large mounting hole.

[0024] Further, the gear transmission assembly contains four sets of gear transmission groups.

[0025] Each set of gear transmission groups comprises a gear shaft, a rudder shaft, a driven gear, a transmission gear bearing and a positioning sleeve.

[0026] In each set of gear transmission groups, the rudder shaft is mounted in the large mounting hole, and the bearing for fixing the rudder shaft and the driven gear are sequentially arranged on the shaft from inside to outside; the transmission gear and the positioning sleeve are sequentially sleeved on the gear shaft and then screwed into the small mounting hole for fixation.

[0027] The transmission gear is meshed with the driving gear and the driven gear respectively.

[0028] Further, the exposed part of the rudder shaft of the gear transmission assembly is in a waist shape and is provided with a hole for connecting the rudder.

[0029] The rudders are arranged in a cross shape around the whole pneumatic rudder control device, and the rudders are provided with countersunk holes and waist-shaped grooves at the wing roots; during assembly, the waist-shaped hole and the waist-shaped shaft are matched, and a screw is used for fixation.

[0030] The present application is mainly directed to the control cabin section of the command guidance rocket, i.e., the rudder cabin of the command guidance rocket, in particular the mechanical structure part. The rudder cabin structure is compact and short in length, realizes low cost and miniaturization, and can be used on a small rocket platform.

[0031] Since the flight performance is reduced for the low, slow and small target, the finished servo motor is selected to control the rudder in the present application. In order to save the space on the missile, the pull rod commonly used for the servo motor is not used to control the rudder, but the gear transmission mode is used, and the strength of the transmission mechanism is ensured. The whole rudder cabin section is divided into three assemblies for facilitating assembly. The parts are all standard parts produced in batches, thereby reducing the cost. BRIEF DESCRIPTION OF DRAWINGS

[0032] Figure 1 is the overall schematic view of the rudder cabin structure of the present application;

[0033] Figure 2 is the schematic view of the assembly relationship of each section of the rudder cabin of the present application;

[0034] Figure 3 is the schematic view of the structure of the rudder shell A of the present application;

[0035] Figure 4 is the schematic view of the assembly relationship of the assembly A of the rudder cabin of the present application;

[0036] Figure 5 This is a schematic diagram of the servo motor housing B structure of the present invention;

[0037] Figure 6 This is a schematic diagram of the assembly relationship of the steering gear compartment component B of the present invention;

[0038] Figure 7 This is a schematic diagram of the intermediate base structure of the present invention;

[0039] Figure 8 This is a schematic diagram of the gear shaft assembly relationship of the gear transmission component of the present invention;

[0040] Figure 9 This is a schematic diagram of the assembly relationship of the rudder shaft in the gear transmission assembly of the present invention;

[0041] Figure 10 This is a schematic diagram of the control and transmission of a single rudder blade in this invention;

[0042] Figure 11 This is a schematic diagram of the assembly relationship between a single rudder blade and a single rudder blade control mechanism of the present invention;

[0043] Figure 12 This is an overall schematic diagram of the present invention;

[0044] The attached diagram lists the components represented by each number as follows:

[0045] 1. Servo housing A; 2. Intermediate base; 3. Servo housing B; 4. Rudder; 5. Finished servo motor; 6. Drive gear; 7. Gear shaft; 8. Rudder shaft; 9. Driven gear; 10. Transmission gear; 11. Bearing; 12. Positioning sleeve; 13. Servo housing assembly A; 14. Gear transmission assembly; 15. Servo housing assembly B; 16. Servo motor control board. Detailed Implementation

[0046] To make the objectives, technical solutions, and advantages of this application clearer, the embodiments of this application will be described in further detail below with reference to the accompanying drawings.

[0047] The technical solution will be described in detail below with reference to the accompanying drawings.

[0048] Combination Figure 1 , Figure 2 Its maximum diameter is 57mm, and its total length is 102mm. It is made entirely of engineering plastic and connects to the guided rocket via threaded holes at both ends. The entire servo housing includes servo housing component A 13, gear transmission component 14, servo housing component B 15, and servo blades 4. It is cylindrical in shape, arranged sequentially from top to bottom as described above, with four servo blades evenly distributed around its perimeter in a cross shape.

[0049] like Figure 2As shown, the upper end of the rudder cabin assembly A 13 and the rudder cabin assembly B 15 is circumferentially distributed with 4 threaded holes, and the lower end is circumferentially distributed with 2 threaded holes. The gear transmission assembly 14 has a counterbore at the upper and lower ends. The cabin segments are connected by circumferential screws. The rudder cabin assembly A 13, the gear transmission assembly 14, and the rudder cabin assembly B 15 are arranged in a stacked manner from top to bottom. The rudder blades are circumferentially arranged along the outer contour of the middle base assembly. They are fixedly connected to the exposed rudder blade shaft mounting positions on the middle base assembly through screws near the wing roots.

[0050] As shown, Figure 3 The rudder housing A 1 is generally cylindrical in shape. A pair of centrally symmetric grooves are provided inside for arranging the finished servo motor 5. Threaded holes are circumferentially arranged around the rudder housing A 1. The lead wires of the rudder pass through the through-holes and are connected to the circuit control board on the back of the rudder cabin A after passing through the through-holes.

[0051] As shown, Figure 4 The rudder cabin assembly A 13 is cylindrical in shape as a whole, and includes the rudder housing A 1, the finished servo motor 5, and the drive gear 6. The drive gear 6 is connected to the finished servo motor 5 through screws, and the torque is transmitted from the output shaft of the finished servo motor 5 to the drive gear 6 through the spline provided on the transmission shaft of the finished servo motor 5.

[0052] As shown, Figure 4 The drive gear 6 is sleeved on the output shaft of the finished servo motor 5 and fixed by screws. After the finished servo motor 5 and the drive gear 6 are assembled, they are inserted into the corresponding grooves of the rudder housing B 3. Four finished servo motors 5 are required to be installed in the three-degree-of-freedom rudder cabin. Each finished servo motor 5 controls one rudder blade 4, and the installation method is the same.

[0053] As shown, Figure 5 , Figure 6 The rudder housing B 3 is generally cylindrical in shape. The internal structure is generally the same as that of the rudder housing A 1, but the rudder housing B 3 does not have a through-hole. The rudder cabin assembly B 15 is cylindrical in shape as a whole, and includes the finished servo motor 5, the drive gear 6, and the rudder housing B 3. The internal assembly relationship is the same as that of the rudder cabin assembly A 13.

[0054] As shown, Figure 7 The middle base 2 is cylindrical in shape. There are two shaft mounting hole positions every four quarters. One set of mounting hole positions is located at the middle position of the entire assembly, and the other set of smaller mounting hole positions is divided into two groups. Each group is centrally symmetric. One group is located above the left of the middle mounting hole position, and the other group is located below the right of the middle mounting hole position.

[0055] Specifically; as shown, Figure 8 , Figure 9As shown, the gear transmission assembly 14 contains 4 sets of gear transmission groups, each of which includes a gear shaft 7, a rudder shaft 8, a driven gear 9, a transmission gear 10, a bearing 11 and a positioning sleeve 12. In each gear transmission system, the driving gear 9 is engaged with the transmission gear 10, and the transmission gear 10 is engaged with the driven gear 12. The transmission gear 10 is installed on the gear shaft 7, and the left side is limited by the positioning sleeve 12; the driven gear 9 should be installed on the rudder shaft 8, and the left and right sides are limited by the positioning sleeve 12. The assembled rudder shaft 8 should be fixed in the four holes opened in the circumferential direction of the middle base 2, and the assembled gear shaft 7 should be fixed in the four smaller mounting holes opened in the circumferential direction of the middle base 2;

[0056] As shown in the figure, Figure 10 Figure 10 is the X-axis positive rudder transmission mechanism, and the remaining three rudder control mechanisms are the same. The finished servo motor 5 provides torque to the driving gear 6, the driving gear 6 is engaged with the transmission gear 10, and the transmission gear 10 is engaged with the driven gear 9. The driven gear 9 is provided with a D-shaped hole in the center, which cooperates with the rudder shaft 8 and transmits torque to the rudder shaft 8. The rudder 4 is provided with a hole in the center, which cooperates with the rudder shaft and is fixed with the rudder shaft using a countersunk screw.

[0057] As shown in the figure, Figure 11 The rudder 4 is arranged in the middle of the gear transmission assembly 14. After the gear transmission assembly 14 is assembled, the exposed part of the rudder shaft 8 is a waist type, and a hole is provided for connecting the rudder 4. The rudders 4 are arranged in a "cross" shape around the entire pneumatic rudder control device, and the rudders 4 are provided with a countersunk hole and a waist-shaped groove at the wing root. During assembly, the waist-shaped hole and the waist-shaped shaft are matched, and a screw is used for fixation.

[0058] The following embodiments are described in detail below:

[0059] As shown in the figure, Figure 12 The servo motor control board 16 is fixedly connected to the bottom of the rudder cabin assembly A 13 by screws. In actual installation, the control line and power line of the finished servo motor 5 extend to the servo motor control board 16 at the bottom of the rudder cabin assembly A 13 through the wire hole provided on the rudder housing A 1, and are connected to the pins designed in advance on the servo motor control board 16.

[0060] The above-described embodiments of the present application do not constitute a limitation on the scope of protection of the present application.​

Claims

1. A small, low-cost three-channel servo gear compartment mechanism, characterized in that, The steering gear compartment mechanism includes: Servo housing assembly A (13), gear transmission assembly (14), servo housing assembly B (15), rudder blade (4); The servo housing assembly A (13), gear transmission assembly (14), and servo housing assembly B (15) are stacked from top to bottom. The servo housing mechanism is cylindrical in shape and is arranged from top to bottom in the order of servo housing component A (13), gear transmission component (14), and servo housing component B (15); four servo blades (4) are evenly distributed around the servo housing mechanism in a cross shape. The servo housing assembly A (13) and servo housing assembly B (15) are centrally symmetrical in structure; the servo housing assembly A (13), gear transmission assembly (14), and servo housing assembly B (15) are fixedly connected by circumferential screws; the rudder blade (4) is circumferentially arranged along the outer contour of the intermediate base assembly and is fixedly connected to the rudder blade shaft mounting position exposed on the intermediate base assembly by screws near the wing root.

2. The small, low-cost three-channel servo gear compartment mechanism according to claim 1, characterized in that, Servo housing assembly A (13) and servo housing assembly B (15) are respectively inserted into the upper and lower ends of the gear transmission assembly (14); The upper end of the servo gear compartment assembly A (13) and the lower end of the servo gear compartment assembly B (15) are evenly distributed with four threaded holes, and the lower end is evenly distributed with two threaded holes. The gear transmission assembly (14) has countersunk holes at both ends. The compartments are fixedly connected by circumferential screws.

3. The small, low-cost three-channel servo gear compartment mechanism according to claim 1, characterized in that, The servo housing assembly A (13) includes the servo housing A (1), the finished servo motor (5), and the drive gear (6); The drive gear (6) is connected to the finished servo motor (5) by screws; The finished servo motors (5) are arranged in an alternating manner and placed in the pre-set mounting slot of the servo housing A (1) in a centrally symmetrical manner. The two finished servo motors are fixed by installing a gear transmission assembly.

4. The small, low-cost three-channel servo gear compartment mechanism according to claim 3, characterized in that, The servo housing (1) has through holes around its perimeter and threaded holes for mounting the circuit control board on its back. There are four threaded holes evenly distributed around the upper end and two threaded holes evenly distributed around the lower end. The front end is used for fixed connection after being inserted into the base, and the rear end is a connection hole for connecting with other components of the missile.

5. The small, low-cost three-channel servo gear compartment mechanism according to claim 3, characterized in that, The servo cockpit assembly B (15) is cylindrical in shape and includes: Finished servo motor (5), drive gear (6), servo housing B (3); the assembly relationship of finished servo motor (5), drive gear (6), and servo housing B (3) is the same as that of servo housing component A (13).

6. The small, low-cost three-channel servo gear compartment mechanism according to claim 1, characterized in that, The central base (2) is cylindrical in shape, and its interior is divided into four symmetrical quadrants in terms of space. Each quadrant has two mounting holes for the shafts; the two mounting holes for the shafts are of different sizes. The large mounting hole is located in the middle of the entire intermediate base (2); the position of the small mounting hole is determined according to the position of the finished motor and the size of the gear, and is set next to the large mounting hole.

7. The small, low-cost three-channel servo gear compartment mechanism according to claim 6, characterized in that, The gear transmission assembly (14) includes four sets of gear transmission groups; Each gear transmission assembly includes a gear shaft (7), a rudder shaft (8), a driven gear (9), a transmission gear (10), a bearing (11), and a positioning sleeve (12); In each gear transmission group, a rudder shaft (8) is installed in the large mounting hole. From the inside to the outside of the shaft, there are bearings (11) for fixing the rudder shaft (8) and driven gears (9). The transmission gears (10) and positioning sleeves (12) are then screwed into the small mounting holes for fixing on the gear shaft (7). The transmission gear (10) meshes with the drive gear (6) and the driven gear (9) respectively.

8. The small, low-cost three-channel servo gear compartment mechanism according to claim 7, characterized in that, The exposed part of the gear transmission assembly (14) and the rudder shaft (8) is waist-shaped and has holes for connecting the rudder (4); The rudder blades (4) are arranged in a cross shape around the entire aerodynamic rudder blade control device. The rudder blades (4) have countersunk holes and waist-shaped grooves at the wing root. During assembly, the waist-shaped holes and waist-shaped shafts are matched and fixed with screws.

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