Missile booster automatic separation mechanism and separation method thereof

Abstract

The application relates to the technical field of boosters, and discloses a missile booster automatic separation mechanism and a separation method thereof, which comprises a balance tail wing connected with the tail of a missile, an automatic separation mechanism is arranged at the tail of the tail wing, a propeller is arranged at the tail of the automatic separation mechanism, the balance tail wing comprises a tail wing seat, a locking shaft is arranged at the tail of the wing piece to form a synchronous motion relationship with the wing piece, and the unlocking and separation actions of the booster are completed in the unfolding and locking process of the wing piece; the tail wing angle limiting mechanism, the axial limiting mechanism and other components are all centrally designed; the tail wing opening limiting is guaranteed through the shape characteristics of the tail wing seat; the tail wing mechanism components are reduced; the working reliability is improved; the booster not only has the functions of influencing the aerodynamic shape of the missile and improving the flight stability, but also has the self-locking function in the closed state of the tail wing, so that the relative motion between the tail wing mechanism and the missile is prevented when the tail wing mechanism moves in the bore.

Description

TECHNICAL FIELD

[0001] The application relates to the booster technology field, in particular to a missile booster automatic separation mechanism. BACKGROUND

[0002] The booster is a power device containing fuel to push rockets and spaceships into the sky. According to the different fuel used by the booster, the booster can be divided into liquid rocket boosters and solid rocket boosters.

[0003] The sleeve type fork ear support rod structure for a booster disclosed in Chinese Patent Publication No. CN103644784B and the universal booster capable of automatically and undisturbedly falling off disclosed in CN104295407B are generally used for the vertical launching of rockets and are not suitable for launching missiles and boosters from a launching cylinder and improving the stability of missile flight.

[0004] Therefore, the missile booster automatic separation mechanism is needed to launch missiles and boosters from a launching cylinder and improve the stability of missile flight. SUMMARY

[0005] The application aims to provide a missile booster automatic separation mechanism to solve the problems in the background art.

[0006] In order to solve the above technical problems, the application provides the following technical scheme: a missile booster automatic separation mechanism, comprising a balanced tail wing connected with a tail of a missile, wherein an automatic separation mechanism is installed at a tail of the tail wing, a propeller is installed at a tail of the automatic separation mechanism, the balanced tail wing comprises a tail wing seat, a bearing heat shield is arranged in a cavity of the tail wing seat, tail wing positioning pins and tail wing cylindrical pins are movably connected to both sides of an outer surface of the tail wing seat, the tail wing cylindrical pins and the tail wing positioning pins are movably connected to both sides of the outer surface of the tail wing seat, two deep groove ball bearings are installed in a cavity step of the tail wing seat, an inner hexagonal taper end locking screw is arranged at a middle position of the tail wing positioning pin and a corresponding cambered wing, an inner hexagonal flat end locking screw is installed at a top end of the tail wing seat, and a circular clamping groove is formed at a tail end of the tail wing seat.

[0007] The automatic separation mechanism comprises a locking shaft, and a locking screw is arranged on the locking shaft and fixedly connected with the cambered wing.

[0008] A clamping pin is installed at a top of the propeller and is inserted into the inside of the circular clamping groove.

[0009] Preferably, the outer surface of the tail wing seat is provided with a groove, and the width of the scroll wing is adapted to the length of the groove on the outer surface of the tail wing seat.

[0010] Preferably, the bottom of the tail wing seat is provided with an open circular groove between the circular clamping grooves, and the locking shaft penetrates the circular groove.

[0011] Preferably, the scroll wing is equidistantly arranged around the outer surface of the tail wing seat, the scroll wing is an arc-shaped plate, and the scroll wing is folded and attached to the outer surface of the tail wing seat.

[0012] Preferably, the three tail wing cylindrical pins are located in the pin holes of the three screw holes at the front end of the tail wing seat, and the scroll wing and the tail wing torsional spring are constrained.

[0013] Preferably, the inner hexagonal taper end locking screw is located at the middle position of the tail wing positioning pin and the corresponding scroll wing.

[0014] A separation method of a missile booster automatic separation mechanism, comprising the following stages:

[0015] Initial state:

[0016] Before setting the booster separation mechanism to the initial state, the clamping pin of the thruster part is inserted into the circular clamping groove at the bottom of the tail wing seat;

[0017] Then the scroll wing is pushed forward and tightly attached to the surface of the tail wing seat, so that the tail wing seat and the scroll wing are completely attached;

[0018] During the separation process:

[0019] The tail of the scroll wing is fixed with the locking shaft through the locking screw, the scroll wing is unfolded and pressed into the tail wing seat clamping groove under the action of the tail wing torsional spring, and the locking shaft is synchronously rotated, so that the clamping pin on the thruster is unlocked, and because the scroll wing moves backward into the clamping groove, the locking shaft moves backward in the process, so that the thruster is pushed synchronously after being unlocked.

[0020] Compared with the prior art, the beneficial effects achieved by the application are:

[0021] The application adds a locking shaft to the tail of the wing piece, and the wing piece and the locking shaft form a synchronous motion relationship, and the unlocking and separation of the booster are completed during the unfolding and locking of the wing piece, and the structure is simple and reliable.

[0022] The tail wing angle limiting mechanism, axial limiting mechanism and other components are all centrally designed, the tail wing seat is provided with the shape features to ensure the limiting after the tail wing is opened, the tail wing mechanism components are reduced, the working reliability is improved, the tail wing not only has the function of affecting the aerodynamic shape of the missile and improving the flight stability, but also has the self-locking function in the closed state to prevent the relative movement between the tail wing mechanism and the missile in the bore.

[0023] The tail wing positioning pin is fixedly connected with the corresponding arc wing, the tail wing positioning pin protrudes from the front end of the tail wing mechanism in the closed state and is matched with the corresponding hole of the missile, so that the relative rotation between the tail wing mechanism and the missile in the bore is prevented;

[0024] The deep groove ball bearing can ensure the free rotation of the tail wing mechanism of the missile in the flight state and improve the flight stability.

[0025] The heat insulation design is performed, so that the free rotation of the tail wing mechanism is not affected by the thermal deformation of the deep groove ball bearing during the flight of the missile.

[0026] The angle limiting and axial limiting of the arc wing after being opened are ensured through the slope and the groove on the tail wing seat. BRIEF DESCRIPTION OF DRAWINGS

[0027] Figure 1 It is a structural schematic view of the application;

[0028] Figure 2 It is a sectional view of the missile tail wing structure of the application;

[0029] Figure 3 It is a bottom view of the missile tail wing of the application;

[0030] Figure 4 It is a side view of the connection between the missile tail wing and the propeller of the application;

[0031] Figure 5 It is a side view of the missile tail wing of the application

[0032] Figure 6 It is a schematic view of the pin structure on the propeller of the application;

[0033] Figure 7 It is a sectional view of the automatic separation mechanism of the application;

[0034] Figure 8 It is a structural schematic view of the missile tail wing of the application;

[0035] Figure 9 It is a connection diagram of the missile tail wing and the automatic separation mechanism of the application.

[0036] Wherein: 1, tail fin seat; 2, bearing heat shield; 3, arc wing; 4, tail fin positioning pin; 5, tail fin cylindrical pin; 6, tail fin torsional spring; 7, deep groove ball bearing; 8, inner hexagonal taper end set screw; 9, inner hexagonal flat end set screw; 10, propeller; 11, locking pin; 12, locking shaft; 13, set screw. DETAILED DESCRIPTION

[0037] The technical solutions in the embodiments of the application will be clearly and completely described below with reference to the drawings in the embodiments of the application. Obviously, the described embodiments are only part of the embodiments of the application, rather than all the embodiments of the application. Based on the embodiments in the application, all other embodiments obtained by a person of ordinary skill in the art without creative work fall within the protection scope of the application. DETAILED DESCRIPTION

[0039] The embodiment is an embodiment of a missile booster automatic separation mechanism.

[0040] Please refer to Figures 1-9 A missile booster automatic separation mechanism, comprising a balance tail wing connected with the tail of a missile, wherein the tail of the tail wing is provided with an automatic separation mechanism, the tail of the automatic separation mechanism is provided with a propeller 10, the balance tail wing comprises a tail fin seat 1, the inner cavity of the tail fin seat 1 is provided with a bearing heat shield 2, the outer surface of the tail fin seat 1 is movably connected with tail fin positioning pins 4 on both sides, the outer surface of a tail fin cylindrical pin 5 is sleeved with a tail fin torsional spring 6, the tail fin cylindrical pin 5 is movably connected with the outer surface of the tail fin seat 1 on both sides, two deep groove ball bearings 7 are installed in the cavity step of the tail fin seat 1, an inner hexagonal taper end set screw 8 is arranged at the middle position of the tail fin positioning pin 4 and the corresponding arc wing 3, an inner hexagonal flat end set screw 9 is installed at the top end of the tail fin seat 1, and a circular clamping groove is formed at the tail end of the tail fin seat 1.

[0041] The automatic separation mechanism comprises a locking shaft 12, and the locking shaft 12 is fixedly connected with the arc wing 3 through a set screw 13.

[0042] The top of the propeller 10 is provided with a locking pin 11, and the locking pin 11 is inserted into the inside of the circular clamping groove.

[0043] A locking shaft 12 is arranged at the tail of the wing piece, and the locking shaft 12 is in synchronous motion with the wing piece, so that the unlocking and separation of the booster are completed in the unfolding and locking process of the wing piece, and the structure is simple and reliable.

[0044] The tail fin angle limiting mechanism, the axial limiting mechanism and other components are all designed in a centralized manner, the limiting after the tail fin is opened is ensured through the shape characteristics of the tail fin seat 1, the number of components of the whole tail fin mechanism is reduced, the working reliability is improved, the tail fin not only has the functions of affecting the aerodynamic shape of the missile and improving the flight stability, but also has a self-locking function in the closed state, so that the relative motion between the tail fin mechanism and the missile is prevented when the tail fin mechanism moves in the bore. Detailed description

[0046] The embodiment is a separation method of a missile booster automatic separation mechanism.

[0047] A separation method of a missile booster automatic separation mechanism, comprising the following stages:

[0048] Initial state:

[0049] Before setting the booster separation mechanism to the initial state, the latch 11 of the thruster 10 part is inserted into the circular latch slot at the bottom of the tail seat 1;

[0050] Then push the roll wing 3 forward and tightly against the surface of the tail seat 1, so that the tail seat 1 and the roll wing 3 are completely fitted together;

[0051] During the separation process:

[0052] The tail of the roll wing 3 is fixed with the locking shaft 12 by the lock screw 13, the roll wing 3 is unfolded and pressed into the tail seat 1 latch slot under the action of the tail torsion spring 6, driving the locking shaft 12 to rotate synchronously, thereby unlocking the latch 11 on the thruster 10, and because the roll wing 3 moves backward into the latch slot, it drives the locking shaft 12 to move backward during this process, thereby making the thruster 10 push the thruster 10 to separate synchronously after unlocking. Detailed description

[0054] The embodiment is an embodiment of a balance tail wing in a missile booster automatic separation mechanism.

[0055] The application discloses a balance tail wing of a missile booster automatic separation mechanism, which comprises a tail wing seat 1, wherein the tail wing seat 1 is mainly used for restricting the opening angle and axial position of a roll wing 3, is the base of the whole tail wing mechanism, and is internally provided with a bearing heat insulation sleeve 2 which is located between two deep groove ball bearings 7 and mainly plays a heat insulation role for an engine nozzle; the outer surface of the tail wing seat 1 is movably connected with a tail wing positioning pin 4 which is located in a cylindrical hole at the front end of the tail wing seat 1 and is used for restricting the roll wing 3 and a tail wing torsion spring 6 and simultaneously restricting the free rotation of the tail wing mechanism in a closed state; three tail wing cylindrical pins 5 are located in pin holes of three screw holes at the front end of the tail wing seat 1 and are mainly used for restricting the roll wing 3 and the tail wing torsion spring 6; four roll wings 3 are respectively located at the tail wing positioning pin 4 and the three tail wing cylindrical pins 5; the tail wing cylindrical pin 5 and the tail wing positioning pin 4 are of the same nature, except that the tail wing positioning pin 4 is longer than the tail wing cylindrical pin 5 and protrudes from the tail wing seat 1, plays a role of positioning and preventing the tail wing from rotating in the next step of installing parts and is mainly used for improving the flight stability of a missile; the outer surface of the tail wing cylindrical pin 5 is sleeved with the tail wing torsion spring 6; four tail wing torsion springs 6 are respectively located at the middle positions of the tail wing positioning pin 4 and the three tail wing cylindrical pins 5 and are mainly used for ensuring reliable opening of the tail wing after being ejected from a barrel and simultaneously rely on elastic force to make the roll wing 3 be elastically inserted into a wing piece clamping groove in the tail wing seat 1; the tail wing cylindrical pin 5 is movably connected with the two sides of the outer surface of the tail wing seat 1; two deep groove ball bearings 7 are installed in the cavity step of the tail wing seat 1 and are mainly used for free rotation of the tail wing mechanism; the middle position of the tail wing positioning pin 4 and the corresponding roll wing 3 is provided with an inner hexagonal taper end locking screw 8; the middle position of the tail wing cylindrical positioning pin 5 and the corresponding roll wing 3 is provided with an inner hexagonal taper end locking screw 8; the inner hexagonal taper end locking screw 8 is mainly used for ensuring synchronous axial movement of the tail wing cylindrical positioning pin 5 and the roll wing 3 thereon; the top end of the tail wing seat 1 is provided with an inner hexagonal flat end locking screw 9; three inner hexagonal flat end locking screws 9 are located in the three screw holes at the front end of the tail wing seat 1 and are mainly used for restricting axial movement of the tail wing cylindrical pin 5; and a circular clamping groove is formed at the tail end of the tail wing seat 1.

[0056] The outer ring of the deep groove ball bearing 7 is in interference fit with the internal cavity step of the tail wing seat 1.

[0057] The bearing heat insulation sleeve 2 needs to be installed in the tail wing seat 1 before the second deep groove ball bearing 7 is installed.

[0058] The tail wing positioning pin 4 is in clearance fit with the cylindrical hole in the tail wing seat 1.

[0059] The screw hole at the middle position of the outer side of the tail wing positioning pin 4 and the corresponding roll wing 3 is fixedly connected through the inner hexagonal taper end locking screw 8.

[0060] The tail wing cylindrical pin 5 is in clearance fit with the pin hole in the tail wing seat 1.

[0061] One of the two supporting corners of the tail wing torsion spring 6 is supported on the outer circle of the tail wing seat 1, and the other supporting corner is supported on the concave side of the scroll wing 3;

[0062] The hexagonal taper end locking screw 8 and the hexagonal flat end locking screw 9 are coated with thread glue before installation.

[0063] Although embodiments of the invention have been shown and described, it is to be understood that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A missile booster auto-separation mechanism, comprising a tail fin connected to the tail of a missile, said tail fin being provided with an auto-separation mechanism, said auto-separation mechanism being provided with a propeller (10) at its tail, characterized in that: The balance tail wing includes a tail wing seat (1), an inner cavity of the tail wing seat (1) is provided with a bearing heat shield (2), both sides of an outer surface of the tail wing seat (1) are movably connected with a tail wing positioning pin (4) and a tail wing cylindrical pin (5), the tail wing cylindrical pin (5) and the tail wing positioning pin (4) are movably connected with both sides of the outer surface of the tail wing seat (1), two deep groove ball bearings (7) are installed in a cavity step of the tail wing seat (1), a middle position of the tail wing positioning pin (4) and a corresponding scroll wing (3) is provided with a internal hexagonal taper end lock screw (8), a pin hole of the tail wing cylindrical pin (5) at a top end of the tail wing seat (1) is installed with an internal hexagonal flat end lock screw (9), a tail end of the tail wing seat (1) is provided with a circular clamping groove; The automatic separation mechanism includes a locking shaft (12), the locking shaft (12) is provided with a lock screw (13) and is fixedly connected with the scroll wing (3); The top of the propeller (10) is provided with a clamping pin (11), the clamping pin (11) is inserted into the inside of the circular clamping groove; when locking, the clamping pin (11) is connected with the end shape of the locking shaft (12) through clamping.

2. A missile booster auto-separation mechanism according to claim 1, characterized in that: The outer surface of the tail wing seat (1) is provided with a groove, the width of the scroll wing (3) is matched with the length of the groove on the surface of the tail wing seat (1).

3. A missile booster auto-separation mechanism according to claim 1, characterized in that: The bottom of the tail wing seat (1) is provided with an open circular groove between the circular clamping grooves, the locking shaft (12) penetrates out of the circular groove.

4. A missile booster auto-separation mechanism according to claim 1, characterized in that: The scroll wings (3) are equidistantly arranged around the outer surface of the tail wing seat (1), the scroll wings (3) are arc-shaped plates, the scroll wings (3) are folded and attached to the outer surface of the tail wing seat (1).

5. A missile booster auto-separation mechanism according to claim 1, characterized in that: Three tail wing cylindrical pins (5) are located in the pin holes of the three screw holes at the front end of the tail wing seat (1), and the scroll wings (3) and the tail wing torsional springs (6) are constrained.

6. A missile booster auto-separation mechanism according to claim 1, characterized in that: Four tail wing torsional springs (6) are respectively located at the middle positions of the tail wing positioning pins (4) and the three tail wing cylindrical pins (5), and the elastic force generated by the compressed torsional springs after the scroll wings (3) are ejected will make the scroll wings (3) pop into the wing clamping grooves of the tail wing seat (1).

7. A method of separating a missile booster automatic separation mechanism, characterized by: The method includes the following stages: Initial state: Before setting the booster separation mechanism to the initial state, the clamping pin (11) of the propeller (10) is inserted into the circular clamping groove at the bottom of the tail wing seat (1); Then, the scroll wings (3) are pushed forward and tightly attached to the surface of the tail wing seat (1), so that the tail wing seat (1) and the scroll wings (3) are completely attached; the end of the locking shaft (12) is connected with the clamping pin (11) through clamping; During the separation process: The tail part of the scroll wing (3) is fixed with the locking shaft (12) through the lock screw (13), the scroll wing (3) is unfolded and pressed into the clamping groove of the tail wing seat (1) under the action of the tail wing torsional spring (6), and the locking shaft (12) is synchronously rotated, so as to unlock the clamping pin (11) on the propeller (10); because the scroll wing (3) moves backward into the clamping groove, the locking shaft (12) moves backward in the process, so that the propeller (10) is synchronously pushed after being unlocked, and the propeller (10) is separated.

Images