Bullet blocking locking device and design method

Abstract

The invention discloses a bomb blocking and locking device and a design method, the bomb blocking and locking device is installed between a launching tube and a launching power device, the bomb blocking and locking device comprises a flange plate, a locking piece and an anti-rotating pin, and the flange plate is connected with the launching tube and the launching power device through mechanical interfaces; a locking ring face protruding out of the front disc face is coaxially formed on the front disc face of the flange disc, the rear end of the launching tube is matched with the front disc face of the flange disc, and the locking ring face is inserted into the launching tube and matched with the rear end of the aircraft. Locking through holes are distributed in the locking ring face in the circumferential direction and comprise straight-through holes and step through holes which are distributed in a staggered mode. And bullet tail threaded holes matched with the locking through holes in a one-to-one mode are formed in the rear end face of the aircraft, after the aircraft is assembled in the launching tube, the anti-rotating pins are assembled into the corresponding bullet tail threaded holes through the straight through holes, and the locking pieces are assembled into the corresponding bullet tail threaded holes through the step through holes so as to achieve bullet blocking and locking of the aircraft.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft transportation and storage, and particularly relates to a bullet-blocking locking device and a design method thereof. Background Art

[0002] The bullet-blocking locking mechanism is widely used in the transportation and launch systems of aircraft such as rain-enhancing rockets. During storage and transportation, it can play a role in locking and fixing the missile body, avoiding collisions or detachment of the aircraft caused by factors such as vibration and shaking. During launch, it can be unlocked to ensure that the aircraft is launched out of the tube according to the predetermined conditions. It is a mechanism that is crucial for the safety and launch stability of the aircraft.

[0003] The patent application with the publication number CN109764750A provides a locking mechanism for cylindrical products. It installs threaded pins by setting two threaded process holes with an included angle of 180° in the circumferential direction of the aircraft, and cooperates with the circumferential hoop and the guide rail to achieve the locking of the aircraft. This locking mechanism has a simple structure and is convenient for disassembly and assembly. However, by using the method of radially locking the aircraft, it is necessary to correspondingly increase the radial size of the launch tube, which is not conducive to improving the loading density of the aircraft within a certain envelope space.

[0004] The patent application with the publication number CN118565165A provides a pull-off type bullet-blocking locking mechanism, which relies on setting a ring groove on the locking part to achieve precise control of the unlocking force during launch and the stable launch of the aircraft. The locking mechanism provided by this solution has a clear principle and a reliable action process. However, the overall structure is relatively complex and cumbersome, and there are many types of components, which is not conducive to convenient installation and disassembly. Summary of the Invention

[0005] The purpose of the present invention is to provide a bullet-blocking locking device and a design method thereof to overcome the problems existing in the existing transportation and storage mechanisms of aircraft.

[0006] To achieve the above tasks, the present invention adopts the following technical solutions:

[0007] A bullet-blocking locking device, the bullet-blocking locking device is installed between the launch tube and the launch power device. The bullet-blocking locking device includes a flange, a locking part, and an anti-rotation pin. The flange is mechanically connected to the launch tube and the launch power device by mechanical interfaces; wherein:

[0008] A locking ring surface protruding from the front disk surface is coaxially formed on the front disk surface of the flange. The rear end of the launch tube is matched with the front disk surface of the flange, and the locking ring surface is inserted into the launch tube and matched with the rear end of the aircraft;

[0009] The locking ring surface is distributed with locking through holes along the circumferential direction. The locking through holes include straight through holes and stepped through holes that are staggered. On the rear end face of the aircraft, there are formed bullet tail threaded holes that cooperate with the locking through holes one by one. After the aircraft is assembled in the launch tube, the anti-rotation pin is assembled into the corresponding bullet tail threaded hole through the straight through hole, and the locking member is assembled into the corresponding bullet tail threaded hole through the stepped through hole to achieve bullet blocking and locking of the aircraft.

[0010] Further, the locking ring surface is an annular surface protruding from the front disk surface of the flange. The outer diameter of this locking ring surface is smaller than the outer diameter of the flange, and the inner diameter is the same as that of the flange and they are coaxial.

[0011] Further, the anti-rotation pin is assembled into the straight through hole. Its front part is screwed into the bullet tail threaded hole, and the rear part has a clearance fit with the straight through hole.

[0012] Further, the locking member is assembled into the stepped through hole. The locking member includes a locking bolt, an annular stress groove, a protective sleeve, a spherical plain bearing, and a nut. Among them: an annular stress groove is machined on the outer circumference of the middle part of the locking bolt, and a protective sleeve is sleeved outside the annular stress groove; the rear part of the locking bolt is assembled with the spherical plain bearing and the nut; the stepped through hole includes a small diameter part and a large diameter part. The front end of the locking bolt passes through the small diameter part and is screwed into the bullet tail threaded hole, and the protective sleeve is assembled into the small diameter part. The spherical plain bearing and the nut are located in the large diameter part, and the spherical plain bearing is assembled on the stepped surface at the front end of the large diameter part by screwing the nut tightly.

[0013] A design method for a bullet blocking and locking device includes:

[0014] Step 1, design the connection mechanism between the bullet blocking and locking device and the aircraft;

[0015] Step 2, design the mechanical interfaces between the bullet blocking and locking device, the launch tube, and the launch power device, so that the bullet locking device is stably and coaxially connected to the launch tube and the launch power device;

[0016] Step 3, optimize the design of the annular stress groove on the locking bolt, so that the annular stress groove in the middle of the locking bolt only bears the axial load of the aircraft and breaks during launch.

[0017] Further, the mechanical interfaces between the flange and the launch tube and the launch power device are one or more circles of interfaces distributed on the front disk surface and the rear disk surface of the flange.

[0018] Further, the design of the connection mechanism between the bullet blocking and locking device and the aircraft includes:

[0019] Step 1.1, evenly arrange n bullet tail threaded holes on the rear end face of the aircraft;

[0020] Step 1.2: Design the main body of the bullet-blocking and locking device as a flange structure. There is a through hole in the middle of the flange axis. On the front disk surface of the flange, a locking ring surface protruding from the front disk surface is coaxially formed. Along the circumferential direction on the locking ring surface, n locking through holes corresponding to the bullet-tail threaded holes one by one are distributed. The locking through holes include straight through holes and stepped through holes distributed alternately.

[0021] Step 1.3: Design the locking bolt of the locking part. Among them, external threads are machined at both the front end and the rear end of the locking bolt. The external thread at its front end is assembled into the bullet-tail threaded hole, and the other end is located in the stepped through hole.

[0022] Step 1.4: Use an anti-rotation pin to achieve the circumferential rotation limit of the aircraft. The anti-rotation pin is designed with a front threaded end and a rear smooth rod end structure. The front threaded end is assembled into the bullet-tail threaded hole, and the rear smooth rod end is located in the straight through hole.

[0023] Step 1.5: The number of locking parts and anti-rotation pins is the same and both are n / 2.

[0024] Step 1.6: Design the minimum wall gap between the aircraft and the launch tube 、the gap between the rear smooth rod end of the anti-rotation pin and the straight through hole on the locking ring surface 、the gap between the locking bolt and the narrow-diameter part of the stepped through hole on the locking ring surface The three have the following relationship:

[0025] (1);

[0026] Step 1.7: According to the requirement that the locking bolt does not break under the maximum axial overload during the transportation of the aircraft, design the locking force that the locking bolt can provide. An annular stress groove is designed on the outer circumference in the middle of the locking bolt to ensure that the locking bolt can be reliably broken at the annular stress groove during launch, realizing the unlocking between the aircraft and the bullet-blocking and locking device.

[0027] Furthermore, the design of the locking force that the locking bolt can provide includes:

[0028] The locking force that the locking bolt can provide should meet the following requirements:

[0029] (2);

[0030] In the formula, is the maximum axial overload coefficient during the transportation of the aircraft, is the transportation safety factor, is the mass of the aircraft, is the acceleration of gravity, and n is the number of bullet-tail threaded holes.

[0031] Furthermore, the cross-sectional diameter of the annular stress groove and the thrust generated by the launch power device should satisfy the following relationship:

[0032] (3);

[0033] In the formula, is the maximum axial overload coefficient during the launch of the aircraft, is the launch safety factor, is the tensile strength of the material of the locking bolt, is the correlation function between the dynamic tension and static tension of the material of the locking bolt, which is related to the material strain rate and the test temperature and is obtained by fitting and calibration with the actual launch condition data of the aircraft.

[0034] Furthermore, the optimization design of the annular stress groove on the locking bolt is carried out so that only the annular stress groove in the middle of the locking bolt bears the axial load of the aircraft and breaks during launch, including:

[0035] Firstly, a protective sleeve is sleeved outside the annular stress groove; the protective sleeve is made of metal material; secondly, a spherical bearing is installed at the mating part of the rear end of the locking bolt and the step surface of the stepped through hole, and the spherical bearing is assembled to the step surface by assembling a nut on the external thread at the rear end of the locking bolt; when the shear deformation of the locking bolt occurs, the spherical bearing can generate sliding displacement relying on the spherical surface to release the shear stress on the locking bolt.

[0036] An operation and launch system of an aircraft, which uses the bullet-blocking and locking device to carry out bullet-blocking and locking of the aircraft.

[0037] Compared with the prior art, the present invention has the following technical features:

[0038] 1. The present invention realizes the translational displacement constraint along the missile axis and the circumferential rotation constraint around the missile axis of the aircraft through the axial bolt connection method and the shaft-hole fit method, and the overall structure connection principle and connection form have the advantages of simplicity and reliability.

[0039] 2. The present invention adopts the axial locking scheme of the aircraft, which does not occupy the radial space and is beneficial to improving the loading density.

[0040] 3. The present invention optimizes the design of the three clearances between the aircraft and the launch pipe wall, between the anti-rotation pin and the flange through hole, and between the locking bolt and the flange through hole, and can effectively avoid the shear load on the anti-rotation pin and the locking bolt when the aircraft generates an inclined angle.

[0041] 4. The present invention optimizes the design of the locking member, provides an annular stress groove on the locking bolt, and analyzes and calculates its cross-sectional diameter based on transportation overload and launch overload, ensuring the stable and controllable pulling force during launch.

[0042] 5. The present invention optimizes the design of the locking bolt, installs a metal protective sleeve outside its annular stress groove, and adds a spherical plain bearing at the flange mounting end to prevent it from breaking due to shear load and affecting the locking reliability, ensuring that the locking bolt, as the main axial load-bearing member, only bears axial loads. Brief Description of the Drawings

[0043] Figure 1 is a schematic diagram of the installation position of the bullet-blocking locking device;

[0044] Figure 2 is a schematic diagram of the angle generated when the aircraft is placed horizontally;

[0045] Figure 3 is a schematic diagram of the uniformly distributed bullet-tail threaded holes on the rear end face of the aircraft;

[0046] Figure 4 is a schematic diagram of the bullet-blocking locking device;

[0047] Figure 5 is a schematic diagram of the installation of the anti-rotation pin;

[0048] Figure 6 is a schematic diagram of the composition and installation of the locking member.

[0049] Description of the reference numerals in the drawings: 1 launch tube, 2 aircraft, 3 bullet-blocking locking device, 4 launch power device, 21 bullet-tail threaded holes, 31 flange, 32 mechanical interface, 33 locking member, 34 anti-rotation pin, 35 locking ring surface, 311 straight through-hole, 312 stepped through-hole, 331 locking bolt, 332 annular stress groove, 333 protective sleeve, 334 spherical plain bearing, 335 nut. Detailed Embodiment

[0050] The present invention provides a bullet-blocking locking device and a design method, which adopt an axial locking method with the aircraft 2, do not occupy radial space, and effectively improve the loading density. At the same time, the overall structure is simple, with clear and reliable operating principles, convenient disassembly and assembly, etc.

[0051] A bullet-blocking locking device provided by the present invention, as Figures 1 to 6 shown, the bullet-blocking locking device 3 is installed between the launch tube 1 and the launch power device 4. The bullet-blocking locking device 3 includes a flange 31, a locking member 33, and an anti-rotation pin 34. The flange 31 is connected to the launch tube 1 and the launch power device 4 through a mechanical interface 32; wherein:

[0052] A locking ring surface 35 protruding from the front disk surface is coaxially formed on the front disk surface of the flange 31. The rear end of the launch tube 1 is fitted with the front disk surface of the flange 31. The locking ring surface 35 is inserted into the launch tube 1 and cooperates with the rear end of the aircraft 2.

[0053] Locking through holes are distributed along the circumferential direction on the locking ring surface 35. The locking through holes include straight through holes 311 and stepped through holes 312 which are staggered. Threaded holes 21 of the projectile tail are formed on the rear end surface of the aircraft 2 and are in one-to-one cooperation with the locking through holes. After the aircraft 2 is assembled in the launch tube 1, the anti-rotation pin 34 is assembled into the corresponding threaded hole 21 of the projectile tail through the straight through hole 311, and the locking member 33 is assembled into the corresponding threaded hole 21 of the projectile tail through the stepped through hole 312 to realize the bullet-blocking and locking of the aircraft 2.

[0054] Specifically, the locking ring surface 35 is an annular surface protruding from the front disk surface of the flange 31. The outer diameter of the locking ring surface 35 is smaller than the outer diameter of the flange 31, and the inner diameter is the same as that of the flange 31 and they are coaxial. During assembly, the locking ring surface 35 is inserted into the launch tube 1. The outer wall of the locking ring surface 35 is in clearance fit with the inner wall of the launch tube 1. The rear end surface of the launch tube 1 is fitted with the front disk surface of the flange 31 and is connected through the mechanical interface 32, and the locking ring surface 35 also plays a role in radially limiting the launch tube 1.

[0055] See appendix Figure 4 , The locking through holes penetrate through the locking ring surface 35 and the flange 31 to facilitate the installation of the locking member 33 and the anti-rotation pin 34 from the rear to the front. Figure 4 The situation when there are four locking through holes is shown in the example of. Among them, two are straight through holes 311, and the other two are stepped through holes 312. The straight through holes 311 and the stepped through holes 312 are staggered to ensure uniform force during installation positioning. Correspondingly, four threaded holes 21 of the projectile tail are formed on the rear end surface of the aircraft 2.

[0056] See appendix Figure 5 , The anti-rotation pin 34 is assembled into the straight through hole 311. Its front part is screwed into the threaded hole 21 of the projectile tail, and the rear part is in clearance fit with the straight through hole 311 to realize the anti-rotation locking of the aircraft 2.

[0057] See appendix Figure 6, the locking member 33 is assembled into the stepped through hole 312. The locking member 33 includes a locking bolt 331, an annular stress groove 332, a protective sleeve 333, a spherical plain bearing 334, and a nut 335, where: The locking bolt 331 serves as the main axial load-bearing structure in the locking member 33 and is used to connect the flange 31 and the aircraft 2; An annular stress groove 332 is machined on the outer circumference of the middle part of the locking bolt 331, and a protective sleeve 333 is sleeved outside the annular stress groove 332; The rear part of the locking bolt 331 is assembled with the spherical plain bearing 334 and the nut 335; The stepped through hole 312 includes a narrow-diameter part and a wide-diameter part. The front end of the locking bolt 331 passes through the narrow-diameter part and is screwed into the threaded hole 21 at the tail of the projectile, so that the protective sleeve 333 is assembled into the narrow-diameter part. The spherical plain bearing 334 and the nut 335 are located in the wide-diameter part, and the spherical plain bearing 334 is assembled on the stepped surface at the front end of the wide-diameter part by tightening the nut.

[0058] By using the above-mentioned locking member 33 and anti-rotation pin 34, the aircraft 2 can be installed quickly, stably and reliably, with the characteristics of fewer types and quantities of parts, simple overall structure, no occupation of radial space, high disassembly and assembly convenience, and stable and controllable launch break-off force.

[0059] On the basis of the above technical solution, the present invention further provides a design method for a projectile-blocking and locking device, including the following steps:

[0060] Step 1, design the connection mechanism between the projectile-blocking and locking device 3 and the aircraft 2.

[0061] The connection mechanism between the projectile-blocking and locking device and the aircraft 2 should be able to realize the reliable axial connection of the aircraft 2. At the same time, the axial connection method should be able to provide a controllable locking force and ensure the stable unlocking of the aircraft 2 during launch; In addition, the connection mechanism should also have the function of restricting the circumferential rotation of the aircraft 2 around its own axis.

[0062] The connection mechanism includes locking through holes distributed along the circumferential direction on the locking ring surface 35 in the projectile-blocking and locking device 3, and threaded holes 21 at the tail of the projectile on the rear end face of the aircraft 2 that cooperate with the locking through holes one by one. The specific design method is as follows:

[0063] Step 1.1, uniformly arrange n threaded holes 21 at the tail of the projectile on the rear end face of the aircraft 2.

[0064] Step 1.2, design the main body of the projectile-blocking and locking device 3 as a flange 31 structure. The middle part of the axis of the flange 31 has a through hole. A locking ring surface 35 protruding from the front disk surface is coaxially formed on the front disk surface of the flange 31. n locking through holes corresponding to the threaded holes 21 at the tail of the projectile are distributed along the circumferential direction on the locking ring surface 35. The locking through holes include straight through holes 311 and stepped through holes 312 that are staggered.

[0065] Step 1.3: Design the locking bolt 331 of the locking member 33. The front and rear ends of the locking bolt 331 are machined with external threads. The external thread at the front end is assembled into the threaded hole 21 of the projectile tail, and the other end is located in the stepped through-hole 312. Design a spherical plain bearing 334 in the stepped through-hole 312. By assembling a nut 335 onto the external thread at the rear end of the locking bolt 331, the spherical plain bearing 334 is assembled onto the stepped surface to adapt to the axial position offset during the transportation or horizontal placement of the aircraft 2. An annular stress groove 332 is machined on the outer circle of the middle part of the locking bolt, and a protective sleeve 333 is sleeved outside the annular stress groove 332.

[0066] Step 1.4: Use an anti-rotation pin 34 to limit the circumferential rotation of the aircraft 2. The anti-rotation pin 34 is designed with a threaded end at the front and a smooth rod end at the rear. The threaded end at the front is assembled into the threaded hole 21 of the projectile tail, and the smooth rod end at the rear is located in the straight through-hole 311. The circumferential rotation of the aircraft 2 is limited through the shaft-hole fit. A screwdriver slot is machined on the rear end face of the anti-rotation pin 34 to facilitate the tightening of the anti-rotation pin 34.

[0067] Step 1.5: The number of the locking members 33 and the anti-rotation pins 34 is the same and both are n / 2 to ensure uniform force.

[0068] Step 1.6: When the aircraft 2 is transported or stored, it is placed horizontally. Due to the gravity, one side of the aircraft 2 will contact the inner wall of the launch tube 1. With the tail of the aircraft 2 fixed, an angle α will be generated between the axis of the aircraft 2 and the axis of the launch tube 1, as Figure 2 shown.

[0069] To avoid the shear load generated by the angle α of the aircraft 2 on the locking bolt 331 of the locking member 33 and the anti-rotation pin 34, design the minimum clearance between the aircraft 2 and the launch tube 1 the clearance between the smooth rod end at the rear of the anti-rotation pin 34 and the straight through-hole 311 on the locking ring surface 35 the clearance between the locking bolt 331 and the narrow-diameter part of the stepped through-hole 312 on the locking ring surface 35 The three have the following relationship:

[0070] (1);

[0071] The clearance fit relationship in formula (1) can ensure that when the aircraft 2 is placed horizontally and generates an angle α, the contact surface between the aircraft 2 and the launch tube 1 first bears the gravity of the aircraft 2, reducing the load borne by the anti-rotation pin 34 and the locking bolt 331. At the same time, if the aircraft 2 rotates circumferentially, the anti-rotation pin 34 will contact and bear the load with the straight through-hole 311 on the locking ring surface 35 prior to the locking bolt 331, protecting the locking bolt 331 from bearing the shear load.

[0072] In an embodiment of the present invention, the minimum clearance between the barrel wall of the aircraft 2 and the launch tube 1 is 0.5 mm. The clearance between the rear smooth rod end of the anti-rotation pin 34 and the straight through hole 311 on the locking ring surface 35 is designed to be 1 mm, and the clearance between the locking bolt 331 and the narrow diameter part of the stepped through hole 312 on the locking ring surface 35 is designed to be 1.2 mm, meeting the requirements of formula (1) to prevent the locking bolt 331 and the anti-rotation pin 34 from bearing shear loads due to the rotation angle α.

[0073] Step 1.7, according to the requirement that the locking bolt 331 does not break during the maximum axial overload in the transportation process of the aircraft 2, the locking force that the locking bolt 331 can provide should meet the following requirements:

[0074] (2);

[0075] In the formula, is the maximum axial overload coefficient during the transportation of the aircraft 2, is the transportation safety factor, is the mass of the aircraft 2, is the acceleration due to gravity, and n / 2 is the number of locking bolts 331; the material selection and design of the locking bolt 331 are carried out according to the above requirements.

[0076] In an embodiment of the present invention, the mass of the aircraft 2 is 300 kg, and the maximum axial overload coefficient during transportation = 2, and the transportation safety factor is taken as 1.5. According to formula (2), the locking force that the locking bolt 331 can provide needs to be greater than 8820 N; therefore, the locking bolt 331 is made of steel, and the tensile strength of the material is taken as 700 Mpa. According to the cross-sectional stress calculation formula, the cross-sectional diameter of the annular stress groove 332 on the locking bolt 331 needs to be greater than 4 mm.

[0077] In addition, an annular stress groove 332 is designed on the outer circumference of the middle part of the locking bolt 331 to ensure that the locking bolt 331 can be reliably broken at the annular stress groove 332 during launch, realizing the unlocking between the aircraft 2 and the bullet-blocking locking device 3; the cross-sectional diameter of the annular stress groove 332 should satisfy the following relationship with the thrust generated by the launch power device 4:

[0078] (3);

[0079] In the formula, is the maximum axial overload coefficient during the launch of the aircraft 2, is the launch safety factor, is the tensile strength of the material of the locking bolt 331, is the correlation function between the dynamic tension and static tension of the material of the locking bolt 331, which is related to the material strain rate and the test temperature and is obtained by fitting and calibration based on the actual launch condition data of the aircraft 2.

[0080] In an embodiment of the present invention, the maximum axial overload factor during launch = 20, and the launch safety factor takes 1.2. According to formula (3), combined with the correlation function , the cross-sectional diameter of the annular stress groove 332 is calculated to be less than 6.6 mm. Thus, the cross-sectional diameter of the annular stress groove 332 that can provide a reliable locking force during transportation and can be stably broken during launch needs to satisfy mm.

[0081] Step 2, design of the mechanical interface 32 between the bullet-blocking locking device 3 and the launch tube 1 and the launch power device 4.

[0082] As Figure 4 shown, the mechanical interface 32 between the flange and the launch tube 1 and the launch power device 4 can be, for example, one or more circles of interfaces distributed on the front and rear disk surfaces of the flange 31; the interface can be a through hole, a blind hole, a threaded hole, etc., and the stable coaxial connection between the bullet-blocking locking device 3 and the launch tube 1 and the launch power device 4 is realized through a connecting piece, so that the bullet-blocking locking device 3 is fixed when the aircraft 2 is launched.

[0083] Step 3, optimized design of the annular stress groove 332 on the locking bolt 331 to improve the overall reliability.

[0084] To further ensure that the annular stress groove 332 in the middle of the locking bolt 331 is only broken under the axial load of the aircraft 2 during launch, two optimized design schemes are adopted to avoid being sheared and broken under the shear load when the aircraft 2 has other lateral displacements:

[0085] First, a protective sleeve 333 is sleeved outside the annular stress groove 332; the protective sleeve 333 is made of a metal material, and when the locking bolt 331 undergoes shear deformation, it can bear the transmitted shear load prior to the annular stress groove 332, improving the shear resistance of the locking bolt 331, and the sleeved assembly method does not affect the axial load-bearing of the locking bolt 331;

[0086] Second, a spherical plain bearing 334 is installed at the mating part between the rear end of the locking bolt 331 and the stepped surface of the stepped through hole 312, and the spherical plain bearing 334 is assembled onto the stepped surface by assembling a nut 335 on the external thread at the rear end of the locking bolt 331; when the locking bolt 331 undergoes shear deformation, the spherical plain bearing 334 can generate sliding displacement relying on the spherical surface to release the shear stress on the locking bolt 331, further improving the launch stability control.

[0087] The above embodiments are only used to illustrate the technical solutions of the present application, rather than to limit them; although the present application has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: they can still modify the technical solutions recorded in the foregoing embodiments, or perform equivalent replacements on some of the technical features; and these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present application, and should all be included in the protection scope of the present application.

Claims

1. A bullet-proof locking device, characterized in that, The bullet blocking locking device (3) is installed between the launch tube (1) and the launch power device (4), and comprises a flange (31), a locking member (33) and an anti-rotation pin (34). The flange (31) is connected to the launch tube (1) and the launch power device (4) by a mechanical interface (32); wherein: A locking annular surface (35) protruding from the front disk surface is coaxially formed on the front disk surface of the flange (31); the rear end of the launch tube (1) is matched with the front disk surface of the flange (31); the locking annular surface (35) is inserted into the launch tube (1) and matched with the rear end of the aircraft (2); The locking ring surface (35) is provided with locking through holes distributed along the circumferential direction, and the locking through holes include staggered straight through holes (311) and stepped through holes (312); the rear end surface of the aircraft (2) is formed with bullet tail threaded holes (21) that match the locking through holes one by one; after the aircraft (2) is assembled in the launch tube (1), the anti-rotation pin (34) is assembled into the corresponding bullet tail threaded hole (21) through the straight through hole (311), and the locking piece (33) is assembled into the corresponding bullet tail threaded hole (21) through the stepped through hole (312) to achieve bullet blocking and locking of the aircraft (2).

2. The bullet-blocking locking device according to claim 1, wherein, The locking annular surface (35) is an annular surface protruding from the front disk surface of the flange (31). The outer diameter of the locking annular surface (35) is smaller than the outer diameter of the flange (31), and the inner diameter is consistent with the inner diameter of the flange (31) and the two are coaxial.

3. The bullet-blocking locking device according to claim 1, characterized in that, The locking member (33) is assembled into the stepped through hole (312), and the locking member (33) includes a locking bolt (331), an annular stress groove (332), a protective sleeve (333), a joint bearing (334) and a nut (335), wherein: an annular stress groove (332) is processed on the middle outer circumference of the locking bolt (331), and a protective sleeve (333) is sleeved on the outside of the annular stress groove (332); the joint bearing (334) and the nut (335) are assembled at the rear of the locking bolt (331); the stepped through hole (312) includes a thin diameter portion and a wide diameter portion, wherein the front end of the locking bolt (331) passes through the thin diameter portion and is screwed into the tail threaded hole (21) so that the protective sleeve (333) is assembled to the thin diameter portion, the joint bearing (334) and the nut (335) are located in the wide diameter portion, and the joint bearing (334) is assembled on the step surface at the front end of the wide diameter portion by tightening the lock nut.

4. A design method of the bullet-blocking locking device according to claim 3, characterized in that, include: Step 1, designing a connection mechanism between the bullet blocking locking device (3) and the aircraft (2); Step 2, designing a mechanical interface (32) between the bullet blocking locking device (3) and the launch tube (1) and the launch power device (4), so that the bullet blocking locking device (3) and the launch tube (1) and the launch power device (4) are stably and coaxially connected; Step 3, optimizing the design of the annular stress groove (332) on the locking bolt (331) so that the annular stress groove (332) in the middle of the locking bolt (331) is only broken by the axial load of the aircraft (2) during launch.

5. The design method according to claim 4, wherein, The mechanical interfaces (32) between the flange (31), the launch tube (1), and the launch power device (4) are one or more circles of interfaces distributed on the front and rear disk surfaces of the flange (31).

6. The design method according to claim 4, characterized in that The connection mechanism between the designed bullet-blocking and locking device (3) and the aircraft (2) includes: Step 1.1: Uniformly arrange n bullet-tail threaded holes (21) on the rear end face of the aircraft (2). Step 1.2: Design the main body of the bullet-blocking and locking device (3) as a flange (31) structure. The middle of the axis of the flange (31) has a through hole. On the front disk surface of the flange (31), a locking ring surface (35) protruding from the front disk surface is coaxially formed. Along the circumferential direction on the locking ring surface (35), n locking through holes corresponding to the bullet-tail threaded holes (21) one by one are distributed. The locking through holes include straight through holes (311) and stepped through holes (312) distributed alternately. Step 1.3: Design the locking bolt (331) of the locking member (33). Among them, external threads are machined at both the front end and the rear end of the locking bolt (331). The external thread at its front end is assembled into the bullet-tail threaded hole (21), and the other end is located in the stepped through hole (312). Step 1.4: Use an anti-rotation pin (34) to limit the circumferential rotation of the aircraft (2). The anti-rotation pin (34) is designed with a front threaded end and a rear smooth rod end structure. The front threaded end is assembled into the bullet-tail threaded hole (21), and the rear smooth rod end is located in the straight through hole (311). Step 1.5: The number of the locking members (33) and the anti-rotation pins (34) is the same and is n / 2. Step 1.6, design the minimum wall gap between the aircraft (2) and the launch tube (1) and the gap between the rear light rod end of the anti-rotation pin (34) and the straight through hole (311) on the locking ring surface (35) and the gap between the locking bolt (331) and the thin diameter part of the stepped through hole (312) on the locking ring surface (35) The three have the following relationship: (1)； Step 1.7, according to the requirement that the locking bolt (331) will not be broken under the maximum axial overload during the transportation of the aircraft (2), design the locking force that the locking bolt (331) can provide ; an annular stress groove (332) is designed on the outer circumference of the middle part of the locking bolt (331) to ensure that the locking bolt (331) can be reliably broken at the annular stress groove (332) during launch, realizing the unlocking between the aircraft (2) and the bullet-blocking locking device (3).

7. The design method according to claim 6, characterized in that, The design of the locking force that the locking bolt (331) can provide includes: The locking force that the locking bolt (331) can provide shall meet the following requirements: (2)； Wherein, is the maximum axial overload coefficient during the transportation of the aircraft (2), is the transportation safety factor, is the mass of the aircraft (2), is the acceleration due to gravity, and n is the number of the threaded holes (21) at the missile tail.

8. The design method according to claim 7, characterized in that The cross-sectional diameter of the annular stress groove (332) should satisfy the following relationship with the thrust generated by the launch power device (4): (3)； In the formula, is the maximum axial overload coefficient during the launch of the aircraft (2), is the launch safety factor, is the tensile strength of the material of the locking bolt (331), is the correlation function between the dynamic tension and static tension of the material of the locking bolt (331), which is related to the material strain rate and the test temperature and is calibrated by fitting the actual launch condition data of the aircraft (2).

9. The design method according to claim 6, wherein The optimization design of the annular stress groove (332) on the locking bolt (331) is such that the annular stress groove (332) in the middle of the locking bolt (331) is only broken under the axial load of the aircraft (2) during launch, including: Firstly, a protective sleeve (333) is sleeved outside the annular stress groove (332). The protective sleeve (333) is made of a metal material. Secondly, a spherical plain bearing (334) is installed at the mating part of the rear end of the locking bolt (331) and the step surface of the stepped through hole (312). The spherical plain bearing (334) is assembled onto the step surface by assembling a nut (335) onto the external thread at the rear end of the locking bolt (331). When the shear deformation of the locking bolt (331) occurs, the spherical plain bearing (334) can generate a sliding displacement relying on the spherical surface to release the shear stress on the locking bolt (331).

10. An operation and propulsion system of an aircraft, characterized in that, This propulsion system uses the bullet-blocking and locking device according to any one of claims 1 - 3 for bullet-blocking and locking of the aircraft (2).

Images