Variable-dip-angle missile launching test platform

Abstract

The utility model discloses a variable dip angle missile launching test platform, and relates to the technical field of launching test platforms, the variable dip angle missile launching test platform comprises a support frame body, and the support frame body is provided with an adjusting assembly and an unplugging assembly which are matched with each other; the adjusting assembly is arranged at the top of the supporting frame body, comprises a mounting part for mounting a test missile, and is used for adjusting the launching angle of the test missile; the plug-off assembly is arranged on the supporting frame body and located below the adjusting assembly, and the plug-off assembly is provided with a wire adjusting end which stretches out and draws back in the first direction; wherein the wire adjusting end can be in contact with a plug-off wire connected to a test missile; the wire adjusting end drives the plug-off wire to move to adjust the plug-off angle formed between the plug-off wire and the test missile, and therefore plug-off separation of the test missile at different launching angles is achieved. According to the test platform, the launching angle of the test missile can be flexibly adjusted, and the universality and convenience of the test platform are further improved.

Description

TECHNICAL FIELD

[0001] The present application generally relates to the technical field of launch test platform, and particularly relates to a variable-inclination missile launch test platform. BACKGROUND

[0002] The missile launch test platform is a device for conducting missile launch tests, which can simulate various missile launch conditions to test and evaluate the performance of the missile. With the continuous development of missile technology, the demand for missile launch test platforms is also increasing, therefore, it is of great significance to research and develop a general, efficient and stable missile launch test platform.

[0003] The existing missile launch test platform has some problems, for example, many missile test platforms are not convenient to use and transport, have large overall quality, and cannot accurately adjust the launch angle, etc. These problems obviously limit the development of the launch test platform, therefore, the present application provides a variable-inclination missile launch test platform to overcome the above problems. CONTENT OF THE INVENTION

[0004] In view of the above defects or deficiencies in the prior art, it is desirable to provide a variable-inclination missile launch test platform.

[0005] The present application provides a variable-inclination missile launch test platform, comprising:

[0006] A support frame body is provided with an adjusting assembly and a disengaging and inserting assembly that cooperate with each other;

[0007] The adjusting assembly is arranged on the top of the support frame body and comprises a mounting portion for mounting a test missile, and the adjusting assembly is used for adjusting the launch angle of the test missile;

[0008] The disengaging and inserting assembly is arranged on the support frame body and below the adjusting assembly, and the disengaging and inserting assembly has a wire adjusting end that extends and retracts in a first direction;

[0009] The wire adjusting end can be in contact with a disengaging and inserting wire connected to the test missile, and the wire adjusting end adjusts the disengaging and inserting angle between the disengaging and inserting wire and the test missile by moving the disengaging and inserting wire, so as to realize the disengaging and inserting separation of the test missile at different launch angles.

[0010] According to the technical scheme provided by the present application, the adjusting assembly comprises a base and an adjusting portion arranged on the base, and the base is arranged on the top of the support frame body;

[0011] The adjusting part is provided with a barrel mounting seat which forms the mounting part and is used for mounting the test missile; the adjusting part is used for driving the barrel mounting seat to swing, and then adjusting the angle between the barrel mounting seat and the top end face of the support frame body, so as to change the launch angle of the test missile.

[0012] According to the technical scheme provided in the application, the adjusting part comprises a bearing set which is arranged on the base and has a screw rod rotatingly arranged in the bearing set;

[0013] The screw rod is threadedly connected with a screw rod nut seat which is located between the guide rails on the base; a first rotating shaft is further arranged through the screw rod nut seat, and the two ends of the first rotating shaft are respectively rotatingly connected with the end portions of two support rods, and the other end portions of the two support rods are commonly rotatingly connected with the bottom of a fixing seat through a second rotating shaft; the barrel mounting seat is arranged on the side of the fixing seat away from the support rods;

[0014] The bottom surface of the fixing seat is further provided with fixing ears, and the base is provided with connecting plates corresponding to the fixing ears; the connecting plates and the fixing ears are rotatingly connected, and the connecting points of the two are the rotating fulcrums of the fixing seat.

[0015] According to the technical scheme provided in the application, the adjusting part further comprises a driving structure used for driving the screw rod to rotate;

[0016] The driving structure comprises a gear box and a hand wheel which cooperate with each other; the gear box is connected with one end of the screw rod, and the hand wheel transmits the rotation to the screw rod through the gear box.

[0017] According to the technical scheme provided in the application, the disengaging and inserting assembly comprises a mounting plate which is arranged below the side of the support frame body away from the base;

[0018] The mounting plate is provided with an elastic member, and a pulley is arranged on the elastic end of the elastic member; the pulley forms the wire adjusting end, can be in contact with the disengaging and inserting wire under the driving of the elastic member, and adjusts the disengaging and inserting angle between the disengaging and inserting wire and the test missile.

[0019] According to the technical scheme provided in the application, the disengaging and inserting assembly further comprises a rotating member which is arranged at the bottom of the support frame body; the rotating member has a rotating shaft for winding the disengaging and inserting wire; the rotating shaft can release or recover the disengaging and inserting wire, and assists the wire adjusting end to adjust the disengaging and inserting angle.

[0020] According to the technical scheme provided in the application, the support frame body comprises a top plate, a bottom plate and a plurality of connecting rods arranged between the top plate and the bottom plate; the adjusting assembly is arranged on the top plate, the disengaging and inserting assembly is arranged on the side of the top plate away from the adjusting assembly, and a plurality of lightening holes are formed in the bottom plate.

[0021] To sum up, the technical scheme specifically discloses a variable-inclination missile launching test platform, which comprises a support frame body, an adjusting assembly and a disengaging and inserting assembly arranged on the support frame body in cooperation, the adjusting assembly is arranged on the top of the support frame body and comprises a mounting part for mounting a test missile, and the adjusting assembly is used for adjusting the launching angle of the test missile; the disengaging and inserting assembly is arranged on the support frame body and located below the adjusting assembly, and the disengaging and inserting assembly has a wire adjusting end which can be extended or retracted in a first direction; wherein the wire adjusting end can be in contact with a disengaging and inserting wire connected to the test missile; the wire adjusting end adjusts the disengaging and inserting angle between the disengaging and inserting wire and the test missile by driving the disengaging and inserting wire to move, so that the disengaging and inserting separation of the test missile at different launching angles is realized.

[0022] The existing missile launching test platform has problems of inconvenience in use and transportation, large overall quality, and inability to accurately adjust the launching angle, etc., in the application, the adjusting assembly and the disengaging and inserting assembly are arranged, so that the launching angle of the test missile can be flexibly adjusted, and the disengaging and inserting angle between the disengaging and inserting wire and the test missile at the current launching angle can be adjusted by driving the disengaging and inserting wire to move by the wire adjusting end, so that no matter how the test missile is inclined, the disengaging and inserting wire can reach the appropriate disengaging and inserting angle under the driving of the wire adjusting end, and the versatility and convenience of the missile launching test platform are improved. BRIEF DESCRIPTION OF DRAWINGS

[0023] Other features, objects and advantages of the application will become more apparent from the following detailed description of non-limiting embodiments made with reference to the accompanying drawings:

[0024] Figure 1 It is a whole structure schematic view of a variable-inclination missile launching test platform.

[0025] Figure 2 It is a structure schematic view of an adjusting assembly of a variable-inclination missile launching test platform.

[0026] Figure 3 It is a whole structure schematic view of an adjusting assembly of a variable-inclination missile launching test platform.

[0027] Figure 4 It is a launching working condition schematic view of a variable-inclination missile launching test platform.

[0028] The figure labels: 1, support frame body; 2, adjustment assembly; 3, disconnection assembly; 4, test missile; 5, disconnection wire; 6, base; 7, barrel mounting seat; 8, bearing set; 9, screw rod; 10, screw rod nut seat; 11, support rod; 12, fixed seat; 121, fixed lug; 13, gear box; 14, hand wheel; 15, mounting plate; 16, telescopic piece; 17, pulley; 18, rotating piece; 19, top plate; 20, bottom plate; 21, connecting rod; 22, connecting plate; 23, guide rail. DETAILED DESCRIPTION

[0029] The application will be further described below in conjunction with the drawings and embodiments. It can be understood that the specific embodiments described herein are only used to explain the related application, and not to limit the application. In addition, it should be noted that only the parts related to the application are shown in the drawings for ease of description.

[0030] It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other without conflict. The present application will be described in detail below with reference to the drawings and in conjunction with the embodiments.

[0031] Embodiment 1

[0032] In order to make the technical solutions of the embodiments of the present application more clear and easy to understand, the application background of the embodiments of the present application is introduced as follows.

[0033] The missile launch test platform is a device for conducting missile launch tests. It can simulate various missile launch conditions (e.g., different launch angles) to test and evaluate the performance of the missile. Before the missile is launched, the missile is usually connected to the disconnection wire through a special serial port, so as to transmit relevant parameters of the missile to the control system or monitoring system, such as performance parameters, environmental conditions, flight attitude, and thrust, etc. These data are crucial for ensuring the normal operation of the missile and evaluating its performance. The setting of the disconnection wire ensures that these data can be transmitted in real time and used for analyzing and adjusting the launch parameters. After the missile is launched, in order to ensure that the missile will not be dragged by the connector during flight, and to avoid damage to the missile or the connector, whether the disconnection wire can realize rapid and stable disconnection also has a non-negligible influence on the performance test of the missile.

[0034] In view of this, please refer to Figure 1 The overall structure schematic diagram of a variable inclination missile launch test platform provided by the embodiment shown in the figure comprises:

[0035] The support frame body 1 is provided with the adjustment assembly 2 and the disconnection assembly 3 which cooperate with each other;

[0036] The adjusting assembly 2 is arranged on the top of the support frame body 1, and comprises a mounting part for mounting the test missile 4, and the adjusting assembly 2 is used for adjusting the launch angle of the test missile 4.

[0037] The dismounting assembly 3 is arranged on the support frame body 1 and below the adjusting assembly 2, and the dismounting assembly 3 has a wire adjusting end which can be extended and retracted along a first direction.

[0038] The wire adjusting end can be in contact with the dismounting wire 5 connected to the test missile 4, and the wire adjusting end adjusts the dismounting angle between the dismounting wire 5 and the test missile 4 by driving the dismounting wire 5 to move, so that the dismounting separation of the test missile 4 at different launch angles can be realized.

[0039] In the embodiment, the support frame body 1 is used to form the mounting carrier of the adjusting assembly 2 and the dismounting assembly 3, and the support frame body 1 comprises a top plate 19, a bottom plate 20 and a plurality of connecting rods 21 arranged between the top plate 19 and the bottom plate 20, and the specific structure can be referred to Figure 1 ; In order to facilitate the transportation, the top plate 19, the bottom plate 20 and the connecting rods 21 can be assembled in a detachable manner, and in order to reduce the weight, a plurality of weight reduction holes (not shown in the figure) can be formed in the bottom plate 20; in addition, the adjusting assembly 2 is arranged on the support frame body 1, that is, on the top plate 19; as the name implies, the adjusting assembly 2 is used to flexibly adjust the launch angle of the test missile 4 mounted thereon, so that the performance test of the test missile 4 under different launch conditions can be realized; therefore, the adjusting assembly 2 comprises a mounting part for fixedly mounting the test missile 4; the dismounting assembly 3 is also arranged on the support frame body 1, more specifically, the dismounting assembly 3 is arranged at the bottom of the top plate 19, that is, on the side away from the adjusting assembly 2; the wire adjusting end in the dismounting assembly 3 can be extended and retracted along the first direction to contact the dismounting wire 5 connected to the test missile 4, and under the continuous extension, the dismounting wire 5 will be straightened due to the tension and form a stable angle with the test missile 4, that is, the dismounting angle.

[0040] In actual application, due to the different launch angles, the angle between the test missile 4 and the top surface of the support frame body 1 will also be different, and the dismounting wire 5 cannot meet the launch requirements without adjustment, generally, when the dismounting angle is close to about 90°, the dismounting separation of the test missile 4 during the launch process can be successfully realized, so the adjustment of the dismounting wire 5 by the wire adjusting end will also refer to this dismounting angle (which can be adjusted according to the actual situation), and the adjustment process can be understood in combination with Figure 4 ; wherein the first direction in the embodiment refers to the horizontal direction. Figure 4

[0041] In a preferred embodiment, the adjusting assembly comprises a base 6 and an adjusting part arranged on the base 6, and the base 6 is arranged on the top of the support frame body 1. ​

[0042] The adjusting part is provided with a barrel mounting seat 7, which forms a mounting part for mounting the test missile 4. The adjusting part is used to drive the barrel mounting seat 7 to swing, and then adjust the angle between the barrel mounting seat 7 and the top end surface of the support frame body 1, so as to change the launch angle of the test missile 4.

[0043] Specifically, the base 6 in the adjusting assembly is also detachably connected to the top of the support frame body 1. The base 6 forms a mounting surface of the adjusting part, and also facilitates the disassembly and transportation of the entire adjusting assembly. The barrel mounting seat 7 on the adjusting part is the mounting part for fixing the test missile 4 as described above. Different specifications of test missiles 4 can be fixed by means of a lock or a clamping structure, so as to drive the launch angle of the test missile 4 through the control of the adjusting part itself. It should be noted that the change of the launch angle is not limited to the definition of the angle between the barrel mounting seat 7 and the top end surface of the support frame body 1 in the actual application. The specific launch angle can be measured by a scale and directly read out.

[0044] In a preferred embodiment, referring to Figure 2 The adjusting part comprises a bearing set 8, which is arranged on the base 6, and a lead screw 9 rotatably arranged in the bearing set 8.

[0045] The lead screw 9 is threadedly connected with a lead screw nut seat 10, and the lead screw nut seat 10 is located between the guide rails 23 on the base 6. A first rotating shaft is also arranged through the lead screw nut seat 10, and the two ends of the first rotating shaft are rotatably connected with the end portions of a support rod 11, respectively. The other end portions of the two support rods 11 are rotatably connected with the bottom of a fixed seat 12 through a second rotating shaft. The barrel mounting seat 7 is arranged on the side of the fixed seat 12 away from the support rods 11.

[0046] The fixed seat 12 is further provided with fixed ears 121 on the bottom surface of the two sides. The base 6 is provided with a connecting plate 22 corresponding to the fixed ears 121. The connecting plate 22 and the fixed ears 121 are rotatably connected, and the connecting point of the two is the rotating support point of the fixed seat 12.

[0047] Specifically, the adjusting part comprises a bearing set 8 arranged on the base 6, the bearing set 8 is composed of front and rear bearings arranged along the first direction, the two bearings are used to support the rotation of the lead screw 9, under the rotation of the lead screw 9, the lead screw nut base 10 moves linearly along the guide rail 23, the extension direction of the guide rail 23 is also along the first direction, the bottom of the lead screw nut base 10 is located in the guide rail 23, and the guide rail 23 further provides movement guidance for the lead screw nut base 10; a first rotating shaft is further arranged on the lead screw nut base 10, the two rotating connections of the first rotating shaft are provided with support rods 11, the support rods 11 can rotate under the driving of the lead screw nut base 10; in addition, the support rods 11 are arranged obliquely between the base 6 and the fixed seat 12, so that when the lead screw nut base 10 drives the support rods 11 to move, the end of the support rods 11 connected with the fixed seat 12 will lift the fixed seat 12 on which the test missile 4 is mounted, and the fixed lug 121 rotates around the connecting shaft connected with the connecting plate 22, which is equivalent to rotating the test missile 4 around the connecting plate 22. Figure 2 to Figure 4 , so that the adjustment of the launch angle is completed.

[0048] It needs to be explained that, referring to Figure 3 , the adjusting part further comprises: a driving structure for driving the rotation of the lead screw 9; in the embodiment of the application, the driving structure comprises: a gear box 13 and a hand wheel 14 cooperating with each other; the gear box 13 is connected with one end of the lead screw 9, and the hand wheel 14 transmits the rotation to the lead screw 9 through the gear box 13.

[0049] In actual application, the hand wheel 14 is usually connected with a pinion or a worm gear through a set screw or other fixing device, and then the pinion or the worm gear is engaged with a large gear in the gear box 13, the gear box 13 can increase the torque when the hand wheel 14 rotates, so that the operation is more labor-saving, and at the same time, a slower rotation speed can be realized, so as to ensure the accuracy of the launch angle during adjustment.

[0050] In a preferred embodiment, referring to Figure 1 and Figure 4 , the plug-in and plug-out assembly 3 comprises: a mounting plate 15 arranged below the side of the support frame body 1 away from the base 6.

[0051] The mounting plate 15 is provided with an expansion piece 16, and the expansion end of the expansion piece 16 is provided with a pulley 17, the pulley 17 forms a wire adjusting end, can be contacted with the plug-in and plug-out wire 5 under the driving of the expansion piece 16, and adjusts the plug-in and plug-out angle between the plug-in and plug-out wire 5 and the test missile 4.

[0052] Specifically, the dismounting assembly 3 comprises a mounting plate 15 for providing a mounting space for a telescopic member 16, i.e. a driving source for realizing the telescopic adjustment of the wire end, and the telescopic member 16 can be a pneumatic cylinder. In order to more conveniently contact the dismounting wires 5, the telescopic end of the telescopic member 16 is provided with a pulley 17 for contacting the dismounting wires 5, and the pulley 17 is generally provided with a smooth groove in the middle for better contacting a larger number of dismounting wires 5 and reducing the damage to the dismounting wires 5.

[0053] Further, when facing the test missile 4 with a large launch angle, blindly stretching the dismounting wires 5 will certainly tear the dismounting wires 5, so the dismounting assembly 3 further comprises a rotating member 18 arranged at the bottom of the support frame body 1, which can be a motor and has a rotating shaft for winding the dismounting wires 5, and the rotating member 18 controls the rotating shaft to rotate in the forward direction or the reverse direction under the rotating instruction to release or recover the dismounting wires 5, so as to better assist the wire end in adjusting the dismounting angle, for example, when adjusting from a large angle to a small angle, a certain amount of dismounting wires 5 can be recovered by controlling the rotating member 18, and then the telescopic member 16 is adjusted to adjust the telescopic amount.

[0054] Based on the above description, the application provides a variable-inclination missile launch test platform, and the specific principle is as follows: first, the test missile 4 is installed on the barrel mounting seat 7, and then the launch angle of the test missile 4 can be adjusted according to the test requirements, and the specific process can be that the hand wheel 14 is rotated to rotate the lead screw 9, so as to control the lead screw nut seat 10 to move along the guide rail 23, and the support rod 11 on the lead screw nut seat 10 will be lifted or lowered to adjust the launch angle of the test missile 4 based on the rotating connection point of the connecting plate 23 and the fixed lug 121, and the action of the fixed seat 12, and when the current launch angle is read by the scale and meets the test requirements, the rotation of the hand wheel 14 is stopped; then, the dismounting wires 5 with an appropriate length are taken out on the rotating member 18 according to the current launch angle of the test missile 4 to connect with the test missile 4, and after the connection is completed, the telescopic member 16 is driven to adjust the dismounting angle between the dismounting wires and the test missile 4 by the pulley 17, so that the dismounting angle meets the dismounting separation of the test missile 4.

[0055] The above description is only the preferred embodiment of the application and the explanation of the applied technical principles. Those skilled in the art should understand that the application range involved in the application is not limited to the technical solutions formed by the specific combination of the above technical features, and also covers other technical solutions formed by any combination of the above technical features or equivalent features without departing from the inventive concept. For example, the above features are replaced with the technical features disclosed in the application (but not limited to) with similar functions to form technical solutions.

Claims

1. A variable angle of attack missile launch test platform characterized by, The utility model relates to a test missile launching support frame, including: Support frame body (1), the support frame body (1) is provided with mutually coordinated adjustment assembly (2) and the plug -in component (3) on it; The adjustment assembly (2) is set up at the top of support frame body (1), and including the installation of test missile (4) installation part, the adjustment assembly (2) is used for adjusting the launch angle of test missile (4); The plug -in component (3) is set up on the support frame body (1), and is located below the adjustment assembly (2), the plug -in component (3) has the wire adjusting end that stretches out and contracts along the first direction; Wherein, the wire adjusting end can be contacted with the plug -in wire (5) connected to the test missile (4);The wire adjusting end adjusts the plug -in angle formed between the plug -in wire (5) and the test missile (4) by driving the plug -in wire (5) to move, so that the test missile (4) realizes the plug -in separation of different launch angles.

2. The variable angle of attack missile launch test platform of claim 1, wherein, The adjustment assembly includes: base (6) and the adjustment part set up on the base (6), the base (6) sets up at the top of support frame body (1); The adjustment part is provided with a barrel mounting seat (7), and the barrel mounting seat (7) forms the installation part for installing the test missile (4);The adjustment part is used for driving the barrel mounting seat (7) to swing, and then adjusts the angle between the barrel mounting seat (7) and the top end surface of the support frame body (1), so as to change the launch angle of the test missile (4).

3. A variable angle of attack missile launch test platform according to claim 2, wherein, The adjustment part includes: bearing group (8), the bearing group (8) is set up on the base (6), and the bearing group (8) is rotatably provided with a lead screw (9) in it; The lead screw (9) is threadedly connected with a lead screw nut seat (10), and the lead screw nut seat (10) is located between the guide rails (23) on the base (6);A first rotating shaft is further provided through the lead screw nut seat (10), and the two ends of the first rotating shaft are rotatably connected with the end portions of a support rod (11) respectively, and the other end portions of the two support rods (11) are rotatably connected to the bottom of a fixed seat (12) through a second rotating shaft;The barrel mounting seat (7) is arranged on the side of the fixed seat (12) away from the support rod (11); The fixed seat (12) bottom surface both sides are further provided with fixed lug (121), the base (6) is provided with the connecting plate (22) corresponding with the fixed lug (121), the connecting plate (22) and the fixed lug (121) rotatable connection, and the connecting point of two is the rotating fulcrum of the fixed seat (12).

4. The variable angle of attack missile launch test platform of claim 3, wherein, The adjustment part further includes: a driving structure for driving the lead screw (9) to rotate; The driving structure includes: mutually coordinated gear box (13) and hand wheel (14);The gear box (13) is connected with one end of the lead screw (9), and the hand wheel (14) transmits rotation to the lead screw (9) through the gear box (13).

5. The variable angle of attack missile launch test platform of claim 2, wherein, The plug -in component (3) includes: mounting plate (15), the mounting plate (15) is set up below the side of the support frame body (1) away from the base (6); The installation plate (15) is provided with a telescopic part (16), a pulley (17) is arranged on the telescopic end of the telescopic part (16), the pulley (17) forms the wire adjusting end, can be contacted with the plug-in wire (5) under the drive of the telescopic part (16), and the plug-in angle between the plug-in wire (5) and the test missile (4) is adjusted.

6. A variable angle of attack missile launch test platform as in claim 5, wherein, The plug-in assembly (3) further comprises a rotating part (18), the rotating part (18) is arranged at the bottom of the support frame (1), the rotating part (18) has a rotating shaft for winding the plug-in wire (5), the rotating shaft can release or recover the plug-in wire (5), and the plug-in angle is adjusted by the wire adjusting end.

7. The variable angle of attack missile launch test platform of claim 1, wherein, The support frame (1) comprises a top plate (19), a bottom plate (20) and a plurality of connecting rods (21) arranged between the top plate (19) and the bottom plate (20); the adjusting assembly (2) is arranged on the top plate (19), the plug-in assembly (3) is arranged on the side, away from the adjusting assembly (2), of the top plate (19), and a plurality of lightening holes are formed in the bottom plate (20).

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