Hoisting deceleration lower stage simulation counterweight device for rocket interstage separation simulation test

Abstract

A lifting deceleration lower stage simulation counterweight device for a rocket stage separation ground simulation test belongs to the technical field of carrier rockets, is used for a stage separation test, and comprises a gantry bracket, a lifting rope, a roller, a damping pulley, a ground rail, a front end socket simulation piece and a shell, the front end socket simulation piece and the shell form a lower stage assembly of the rocket; the lower-rocket stage assembly is connected with the gantry bracket through a lifting rope, so that the central axis of the lower-rocket stage assembly is aligned with the central axis of the test wind tunnel and the central axis of the tested stage section; the lower portion of the gantry support is connected with the idler wheels and the damping pulleys through bolts, the idler wheels are meshed with the ground rail so as to restrain the moving direction of the gantry support, and the damping pulleys generate resistance when moving on the ground rail so as to decelerate the gantry support. The levelness of the ground rail is finely adjusted by adding a gasket. According to the invention, reliable reuse of the lower stage counterweight simulation device when a rocket interstage separation test is carried out on the ground is realized, the repeated test preparation period is shortened, and the test cost is saved.

Description

Technical Field

[0001] The present invention relates to a hoisting and decelerating lower stage simulation counterweight device for rocket interstage separation simulation test, in particular to a hoisting and decelerating lower stage simulation counterweight device for rocket interstage separation ground simulation test and a test method, belonging to the technical field of launch vehicles. Background Art

[0002] In order to reduce the ineffective mass of the structure and improve the carrying efficiency, launch vehicles generally adopt a multi-stage engine series design. During flight, the lower stage engine ignites first, and after the fuel is consumed, the interstage separation is carried out, the lower stage is thrown away, and the upper stage engine is started at the same time for the subsequent flight of the rocket. Interstage separation has the characteristics of large instantaneous load, complex internal flow field, and strong mechanical and thermal coupling, and is one of the key links in the overall design of the rocket.

[0003] In the existing technology, the cost of conducting inter-stage separation tests is high and the test cycle is long, which does not match the actual needs. Summary of the invention

[0004] The technical problem to be solved by the present invention is: to overcome the shortcomings of the prior art and provide a hoisting and decelerating lower stage simulation counterweight device and a test method for a ground simulation test of rocket stage separation. In addition to being able to assess the rocket stage separation process, it can also reflect the pitch, yaw and roll characteristics of the lower stage under the action of the jet. At the same time, the operation method is relatively simple, avoiding the repair work of the deformation structure of the lower stage after each test, and realizing the reliable reuse of the lower stage counterweight simulation device of the stage separation test, shortening the repeated test preparation cycle, and saving the test cost.

[0005] The purpose of the present invention is achieved through the following technical solutions: A hoisting and decelerating lower stage simulation counterweight device for a ground simulation test of rocket stage separation, comprising a gantry bracket, a hoisting rope, a roller, a damping pulley, a ground rail, a front head simulation part, and a shell; The front head simulation part and the shell form the rocket lower stage assembly; the rocket lower stage assembly is connected to the gantry bracket by a suspension rope so that its central axis is aligned with the central axis of the test wind tunnel and the central axis of the test interstage; the lower part of the gantry bracket is connected to the roller and the damping pulley by bolts, the roller engages with the ground rail to constrain the moving direction of the gantry bracket, and the damping pulley generates resistance when moving on the ground rail to slow down the gantry bracket; the ground rail is fine-tuned for horizontality by adding gaskets.

[0006] In one embodiment of the present invention, the portion where the gantry bracket is connected to the suspension rope can be adjusted within a certain range to adjust the yaw, pitch, roll and horizontal position of the rocket lower stage assembly.

[0007] In one embodiment of the present invention, there are multiple rollers and multiple damping pulleys, which are arranged on both sides.

[0008] In one embodiment of the present invention, the front head simulation part is consistent with the aerodynamic shape of the front head of the lower stage engine of a real rocket.

[0009] In one embodiment of the present invention, the front head simulation component is connected to the front end of the shell by using a plurality of axial bolts so as to adapt to the front head simulation components with different aerodynamic shapes.

[0010] A method for simulating the interstage separation of a rocket by hoisting a deceleration lower stage simulation counterweight device for a ground simulation test of interstage separation, comprising: Before the test, the front head simulation parts and the shell are assembled to form the lower stage assembly of the rocket; Connect the gantry bracket to the multiple sets of rollers, and engage the multiple sets of rollers with the ground rails, so as to fix the gantry bracket on the track surface of the ground rails; Use a crane to lift the rocket lower stage assembly to the middle of the gantry support, suspend it at a suitable height, install the lifting rope, and connect the rocket lower stage assembly to the gantry support; adjust the connection position of the lifting rope and the gantry support until the relative position of the rocket lower stage assembly and the test wind tunnel meets the requirements; Lift the interstage to be tested, connect the front part of the interstage to the test wind tunnel, push the gantry bracket forward along the ground track, and connect the front head simulation part on the lower stage assembly of the rocket to the rear part of the interstage to be tested; Install multiple sets of damping pulleys at the bottom of the gantry bracket to ensure that the gantry bracket generates great resistance when moving on the ground rail and can quickly decelerate; The test wind tunnel is started, the interstage to be tested is separated, and the lower stage assembly of the rocket moves backward along the axial direction under the action of aerodynamic load, pulling the gantry support to move backward along the ground track; The gantry bracket gradually slows down until it stops under the action of the damping pulley.

[0011] In one embodiment of the present invention, after the gantry bracket slows down and stops, each component is checked to see if there is no abnormality, and the gantry bracket is pushed forward along the ground rail to the position to be connected, ready for the next test.

[0012] In one embodiment of the present invention, the method can not only provide feedback on the axial motion characteristics, but also provide feedback on the yaw, pitch and roll characteristics of the rocket lower stage assembly after being acted upon by the jet.

[0013] Compared with the prior art, the present invention has the following beneficial effects: (1) During the test, the rocket lower stage assembly of the present invention is connected by a lifting rope. Compared with the traditional connection method in which the rocket lower stage assembly is directly placed on a rigid guide rail, in addition to feedback on the axial motion characteristics, it can also, to a certain extent, feedback on the yaw, pitch and roll characteristics of the lower stage assembly after being affected by the jet, thereby obtaining more test data.

[0014] (2) The present invention generates resistance through the damping pulley, so that the lower stage assembly gradually decelerates during movement. Compared with the traditional method of decelerating by the lower stage assembly hitting the sandbag, the impact during deceleration is reduced, and structural deformation during impact is avoided. The problem of the traditional lower stage assembly needing to be repaired due to structural deformation during repeated tests is avoided, and there is no need to refill the sandbags after each test due to sandbag damage, thereby shortening the repeated test cycle and saving test costs.

[0015] (3) The upper stage simulation part of the present invention is connected to the shell by bolts, and can be adapted to different upper stage simulation parts to simulate the aerodynamic shape of the lower stage front head during the separation between different launch vehicle stages, thereby increasing the test realism. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 Schematic diagram of the rocket's lower stage assembly with rollers, damping pulleys, gantry brackets, suspension ropes and ground rails.

[0017] Figure 2 It is a schematic diagram of the housing.

[0018] Figure 3 Schematic diagram of the front head emulator.

[0019] Figure 4 It is a schematic diagram of the interstage separation test.

[0020] Figure numerals: gantry bracket-1, lifting rope-2, roller-3, damping pulley-4, ground rail-5, front head simulation part-6, shell-7. DETAILED DESCRIPTION

[0021] To make the objectives, technical solutions and advantages of the present invention more clear, the embodiments of the present invention will be further described in detail below with reference to the accompanying drawings.

[0022] In order to fully verify the interstage separation technical solution, test wind tunnels (including shock wave wind tunnels, blast wave tunnels, etc.) are used on the ground to conduct interstage separation simulation tests. The main test products include test wind tunnels, rocket interstage sections, and lower stage simulated counterweight devices. The test wind tunnel can simulate the flow field in the interstage section when the upper stage engine is ignited, and the rocket lower stage simulated counterweight can simulate the shape, weight, center of mass and other characteristics of the actual lower stage. During the test, the wind tunnel is started to simulate the ignition jet of the upper stage engine. Subsequently, the interstage section is cut, the connection between the upper and lower stages is released, and the lower stage simulated counterweight device moves axially backward under the action of the jet, simulating the separation characteristics of the lower stage during actual flight.

[0023] A hoisting and decelerating lower stage simulation counterweight device for a ground simulation test of rocket stage separation comprises a gantry support 1, a hoisting rope 2, a roller 3, a damping pulley 4, a ground rail 5, a front head simulation part 6, and a shell 7. Figure 1and Figure 2 As shown; the front head simulation part 6 and the shell 7 together constitute the rocket lower stage assembly. The rocket lower stage assembly is connected to the gantry support 1 through the suspension rope 2. The part where the gantry support 1 is connected to the suspension rope 2 can be adjusted within a certain range to fine-tune the yaw, pitch, roll and horizontal position of the assembly, and at the same time align its central axis with the central axis of the test wind tunnel and the central axis of the interstage section under test. The lower part of the gantry support 1 is connected to six groups of pulleys by bolts, three groups on each side, each group includes rollers 3 and damping pulleys 4, and the rollers 3 are engaged with the ground rails 5 to constrain the movement direction of the gantry support 1. The damping pulleys 4 generate greater resistance when sliding on the ground rails, so that the gantry support 1 can be quickly decelerated when moving. The ground rails 5 can be fine-tuned for horizontality by adding gaskets. The front head simulation part 6 is consistent with the aerodynamic shape of the front head of the real rocket lower stage engine, so as to simulate as much as possible the flow field in the interstage section after the jet of the upper stage engine hits the front head of the lower stage during the real interstage separation, as shown Figure 3 As shown. The front end of the front head simulation part 6 and the shell 7 are connected by multiple axial bolts to adapt to the front head simulation part 6 with different aerodynamic shapes. The shell 7 is the main structure of the lower stage simulation counterweight device, and its diameter, weight and center of mass characteristics are consistent with the actual lower stage of the rocket verified in practice.

[0024] The working principle of the present invention is: 1. Before the test, the front head simulation part 6 and the shell 7 are assembled on the ground by bolts to form the lower stage assembly of the rocket; 2. Connect the gantry bracket 1 and the roller 3 by bolts, and engage the six groups of rollers 3 with the ground rail 5, so as to fix the gantry bracket 1 on the track surface of the ground rail 5; 3. Use a crane to lift the rocket lower stage assembly in the previous step to the middle of the gantry support 1 and suspend it at a suitable height; 4. Install the lifting rope 2 to connect the rocket lower stage assembly to the gantry support 1; 5. Appropriately loosen the crane and check the coaxiality between the rocket lower stage assembly and the test wind tunnel. If it does not meet the requirements, appropriately tighten the crane, adjust the connection position of the suspension rope 2 and the gantry bracket 1, and then loosen the crane to check the suspension position of the rocket lower stage assembly. Repeat this step until the relative position of the rocket lower stage assembly and the test wind tunnel meets the requirements; 6. Lift the interstage to be tested, connect the front part of the interstage to the test wind tunnel, push the gantry support 1 forward along the ground rail 5, and connect the front head simulation part 6 on the lower stage assembly of the rocket to the rear part of the interstage to be tested by bolts. Figure 4 As shown; 7. Six sets of damping pulleys 4 are installed at the bottom of the gantry bracket 1 by bolts to ensure that the gantry bracket 4 generates great resistance when moving on the ground rail 5 and can quickly decelerate; 8. The test wind tunnel is started, the interstage to be tested is separated, and the lower stage assembly of the rocket moves backward along the axial direction under the action of aerodynamic load, and pulls the gantry support 1 to move backward along the ground rail 5; 9. The gantry support 1 gradually decelerates until it stops under the action of the damping pulley 4; 10. Check the rocket lower stage assembly, gantry bracket 1, ground rail 5 and other components. If there is no abnormality, push the gantry bracket 1 forward along the ground rail 5 to the position to be connected, and prepare for the next test.

[0025] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

[0026] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. A simulated counterweight device for hoisting and decelerating lower stage for ground simulation test of rocket stage separation, characterized in that: It includes a gantry bracket (1), a suspension rope (2), a roller (3), a damping pulley (4), a ground rail (5), a front head simulation part (6), and a shell (7); The front head simulation component (6) and the shell (7) form a rocket lower stage assembly; the rocket lower stage assembly is connected to the gantry support (1) through a suspension rope (2) so that its central axis is aligned with the central axis of the test wind tunnel and the central axis of the test interstage; the lower part of the gantry support (1) is connected to the roller (3) and the damping pulley (4) through bolts, the roller (3) is engaged with the ground rail (5) to constrain the moving direction of the gantry support (1), and the damping pulley (4) generates resistance when moving on the ground rail (5) to decelerate the gantry support (1); the ground rail (5) is finely adjusted for horizontality by adding a gasket.

2. The rocket stage separation ground simulation test hoisting deceleration lower stage simulation counterweight device according to claim 1, characterized in that: The part where the gantry bracket (1) is connected to the suspension rope (2) can be adjusted in position within a certain range so as to adjust the yaw, pitch, roll and horizontal position of the lower stage assembly of the rocket.

3. The rocket inter-stage separation ground simulation test hoisting deceleration lower stage simulation counterweight device according to claim 1, characterized in that: There are multiple rollers (3) and multiple damping pulleys (4), which are arranged on both sides.

4. The rocket inter-stage separation ground simulation test hoisting deceleration lower stage simulation counterweight device according to claim 1, characterized in that: The front head simulation part (6) is consistent with the aerodynamic shape of the front head of the lower stage engine of a real rocket.

5. The rocket inter-stage separation ground simulation test hoisting deceleration lower stage simulation counterweight device according to claim 1, characterized in that: The front head simulation component (6) is connected to the front end of the shell (7) by using a plurality of axial bolts so as to adapt to front head simulation components (6) with different aerodynamic shapes.

6. A method for simulating interstage separation based on the hoisting deceleration lower stage simulation counterweight device for ground simulation test of rocket interstage separation according to claim 1, characterized in that: include: Before the test, the front head simulation component (6) and the shell (7) are assembled to form a rocket lower stage assembly; Connecting the gantry bracket (1) to the plurality of rollers (3), and engaging the plurality of rollers (3) with the ground rail (5), thereby fixing the gantry bracket (1) on the track surface of the ground rail (5); Using a crane to lift the rocket lower stage assembly to the middle of the gantry support (1), suspending it at a suitable height, installing a lifting rope (2), and connecting the rocket lower stage assembly to the gantry support (1); adjusting the connection position of the lifting rope (2) and the gantry support (1) until the relative position of the rocket lower stage assembly and the test wind tunnel meets the requirements; Hoisting the interstage to be tested, connecting the front part of the interstage to the test wind tunnel, pushing the gantry bracket (1) forward along the ground rail (5), and connecting the front head simulation component (6) on the lower stage assembly of the rocket to the rear part of the interstage to be tested; A plurality of damping pulleys (4) are installed at the bottom of the gantry support (1) to ensure that the gantry support (4) generates a large resistance when moving on the ground rail (5) so as to be able to decelerate quickly; The test wind tunnel is started, the interstage to be tested is separated, and the lower stage assembly of the rocket moves backward along the axial direction under the action of the aerodynamic load, and pulls the gantry bracket (1) to move backward along the ground rail (5); The gantry support (1) is gradually decelerated under the action of the damping pulley (4) until it stops.

7. The inter-stage separation simulation test method according to claim 6, characterized in that: After the gantry support (1) slows down and stops, check all parts to see if there is any abnormality. Then push the gantry support (1) forward along the ground rail (5) to the position to be connected, and prepare for the next test.

8. The inter-stage separation simulation test method according to claim 1, characterized in that: In addition to being able to feedback the axial motion characteristics, this method can also feedback the yaw, pitch and roll characteristics of the rocket's lower stage assembly after being affected by the jet.

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