A ground separation test device and test method for a booster rocket

Abstract

The application provides a kind of bundled rocket booster ground separation test device and test method, device includes booster simulation cabin, first steel wire rope, second steel wire rope, gantry, force bearing wall, steel wire rope fixing tool and buffer device;Force bearing wall is used to replace core stage cabin;Booster simulation cabin is obtained by modification from existing launch vehicle cabin;Booster simulation cabin is connected with gantry by first steel wire rope;Booster simulation cabin is connected with steel wire rope fixing tool by second steel wire rope;Booster simulation cabin is connected with force bearing wall by connecting separation mechanism;Buffer device is located in the separation swing direction of booster simulation cabin.The application realizes the simulation of booster horizontal push rotation separation process through ground tool and test auxiliary device, greatly reduces the test cost and shortens the test preparation period under the premise of achieving the purpose of separation mechanism examination.

Description

Technical Field

[0001] This invention relates to the field of space launch vehicle structural design and testing, specifically to a ground separation test device and method for a bundled rocket booster, applicable to ground unlocking and separation test verification of the connection and separation mechanism of a bundled launch vehicle booster. Background Technology

[0002] With the continuous improvement of launch vehicle carrying capacity, clustered launch vehicles have become one of the mainstream development directions. For a new type of solid-propellant clustered launch vehicle, its first stage is clustered with four boosters. The boosters are connected to the core stage through two clustering points, one at the front and one at the rear. A connection / separation mechanism is installed at each clustering point. The main function of the connection / separation mechanism is to connect the core stage and the boosters, fulfilling the connection and unlocking functions of the boosters. The booster separation adopts a horizontal thrust-rotation separation scheme, and the unlocking and separation process proceeds in the following sequence:

[0003] a. The booster's fore and aft side thrusters ignite and initiate rocket propulsion;

[0004] b. The cutting device of the front and rear connection separation mechanism works to unlock the front and rear connection separation mechanism;

[0005] c. Under the thrust of the side thruster rocket, the ball head and ball socket structure in the rear connection separation mechanism successfully detached;

[0006] d. The booster achieves lateral rotational separation in a designed orientation.

[0007] At the moment of booster separation, the thrust difference between the front and rear side thrusters causes the booster to generate an angular acceleration α relative to its center of mass, while the lateral thrust of the front and rear side thrusters causes the booster to generate a lateral acceleration a. The booster's angular acceleration α and acceleration a control its lateral rotational separation at the designed attitude.

[0008] In addition, the booster connection and separation mechanism needs to compensate for the errors caused by the machining and assembly of the rocket body structure during the booster docking process, as well as for the different degrees of displacement and angle caused by factors such as internal pressure, thrust, low temperature, wind resistance, sway, and local thrust loads under conditions such as core stage fueling in the vertical working condition, active phase flight, and core stage towing booster flight.

[0009] Existing ground separation tests of bundled launch vehicle boosters primarily employ actual boosters and core stage products or full-scale simulated modules, using side thrusters as the power source to conduct ground separation tests and assess the accuracy and coordination of the connection and separation mechanism design. This method can accurately simulate the actual booster separation state, but the tests require complete side thrusters, connection and separation mechanisms, structural modules, and complex ground test fixtures. The test conditions are complex, the costs are high, and the test preparation cycle is lengthy. Summary of the Invention

[0010] The purpose of this invention is to provide a ground separation test device and method for bundling rocket boosters, which can accurately simulate the booster separation process while reducing the complexity and cost of the test.

[0011] To achieve the above objectives, the present invention provides a ground separation test device for a rocket booster, comprising a booster simulation chamber, a first steel wire rope, a second steel wire rope, a gantry frame, a load-bearing wall, a steel wire rope fixing fixture, and a buffer device; the load-bearing wall is used to replace the core stage chamber; the booster simulation chamber is modified from an existing launch vehicle chamber; the booster simulation chamber is connected to the gantry frame via the first steel wire rope; the booster simulation chamber is connected to the steel wire rope fixing fixture via the second steel wire rope; the booster simulation chamber is connected to the load-bearing wall via a separation mechanism; and the buffer device is located in the separation swing direction of the booster simulation chamber.

[0012] In the aforementioned ground separation test device for a rocket booster, the connection point of the second steel wire rope to the booster simulation cabin is at the same height as the center of mass of the booster simulation cabin; the distance between the connection point of the first steel wire rope to the booster simulation cabin and the connection point of the second steel wire rope to the booster simulation cabin is H, and the connection point of the first steel wire rope to the booster simulation cabin is located above the connection point of the second steel wire rope to the booster simulation cabin.

[0013] The aforementioned ground separation test device for a rocket booster includes two first steel wire ropes, the connection points of which are located on the same diameter as the booster simulation cabin; and two second steel wire ropes, the connection points of which are located on the same diameter as the booster simulation cabin.

[0014] The aforementioned ground separation test device for a rocket booster is provided with a first tension control device on each first steel wire rope, which controls the tension so that the tension of the two first steel wire ropes is the same; and a second tension control device is provided on each second steel wire rope, which controls the tension so that the tension of the two second steel wire ropes is the same.

[0015] The aforementioned ground separation test device for a rocket booster includes a buffer device with a distance of L between it and the booster simulation chamber, and a distance of L between the axis of the booster simulation chamber and the mounting point of the first steel wire rope on the gantry.

[0016] The above-mentioned ground separation test device for a bundled rocket booster, wherein the arrangement of the ground separation test device satisfies the following conditions:

[0017] 1)2F1·Sinθ·H=J z ·α

[0018] 2)2F2·Cosβ+2F1·Sinθ=m·a

[0019] 3)2F2·Sinβ+m·g-2F1·Cosθ=m·a1

[0020] Where θ is the angle between the first wire rope and the axis of the booster simulated cabin, β is the angle between the second wire rope and the horizontal direction, m is the mass of the booster simulated cabin, F1 is the tension in the first wire rope, F2 is the tension in the second wire rope, and J z Let α be the moment of inertia of the booster simulation cabin about its center of mass horizontal axis, α be the rotational angular acceleration when the booster unlocks and separates, a be the lateral acceleration when the booster unlocks and separates, and a1 be the relative axial acceleration when the booster unlocks and separates; H be the distance between the connection point of the first wire rope and the booster simulation cabin and the connection point of the second wire rope and the booster simulation cabin.

[0021] Another technical solution provided by the present invention is a ground separation test method for a strapped rocket booster, which uses the above-mentioned ground separation test device for a strapped rocket booster. The ground separation test method includes:

[0022] 1) Based on the transverse thrust rotation separation attitude designed for the bundled launch vehicle booster, and the calculation formula 1) 2F1·Sinθ·H=J z ·α;2)2F2·Cosβ+2F1·Sinθ=m·a;3)2F2·Sinβ+m·g-2F1·Cosθ=m·a1 Calculate the relevant design parameters F1, F2, θ, β, H, where θ is the angle between the first wire rope and the axis of the booster simulated cabin, β is the angle between the second wire rope and the horizontal direction, m is the mass of the booster simulated cabin, F1 is the tension of the first wire rope, F2 is the tension of the second wire rope, J z Let H be the moment of inertia of the booster simulator about its center of mass horizontal axis, and let H be the distance between the connection point of the first wire rope to the booster simulator and the connection point of the second wire rope to the booster simulator.

[0023] 2) Arrange the ground separation test device for the bundled rocket boosters according to the relevant design parameters obtained from the calculation;

[0024] 3) Connect the power supply and test cables of the front connection separation mechanism and the rear connection separation mechanism, and complete the preparation of test and auxiliary equipment;

[0025] 4) After the unlocking command is issued, the front connection separation mechanism and the rear connection separation mechanism are unlocked, and the booster simulates the cabin to separate and swing out in the designed attitude.

[0026] 5) Observe, collect and analyze the status and test data of the front and rear connection separation mechanisms after unlocking, and complete the ground separation test.

[0027] The above-mentioned method for ground separation test of a rocket booster includes step 2) comprising: connecting the booster simulation chamber to the load-bearing wall via a front connection separation mechanism and a rear connection separation mechanism; connecting the booster simulation chamber to the gantry via two first steel wire ropes, the first steel wire ropes having an angle of θ with the axis of the booster simulation chamber, and controlling the tension of the first steel wire ropes to F1 via a first tension control device; connecting the booster simulation chamber to the steel wire rope fixing fixture via two second steel wire ropes, the second steel wire ropes having an angle of β with the horizontal direction, and controlling the tension of the second steel wire ropes to F2 via a second tension control device; and placing a buffer device in the separation swing direction of the booster simulation chamber.

[0028] In the above-mentioned method for ground separation test of a rocket booster, the distance L between the buffer device and the booster simulation cabin is consistent with the distance L between the axis of the booster simulation cabin and the installation point of the first steel wire rope on the gantry; the distance M between the bottom of the booster simulation cabin and the ground should ensure that the booster simulation cabin does not collide with the ground during the swinging process after unlocking.

[0029] Compared with the prior art, the beneficial technical effects of the present invention are:

[0030] This invention provides a ground separation test device and method for a bundled rocket booster, which realizes the simulation of the booster's horizontal rotation separation process through ground tooling and test auxiliary devices. Under the premise of achieving the test objectives of the separation mechanism, it greatly reduces the test cost and shortens the test preparation cycle. Attached Figure Description

[0031] The ground separation test apparatus and test method for the bundled rocket booster of the present invention are given in the following embodiments and figures.

[0032] Figure 1 This is a schematic diagram of the ground separation test device for a bundled rocket booster according to an embodiment of the present invention.

[0033] Figure 2 This is a schematic diagram showing the connection between the wire rope and the booster simulation cabin in an embodiment of the present invention. Detailed Implementation

[0034] The following will combine Figures 1-2 The ground separation test apparatus and test method for the bundled rocket booster of the present invention are described in further detail.

[0035] In this invention, a side-thrust rocket is used as the power source for the separation of the attached rocket booster, employing a horizontal thrust-rotation separation scheme. The purpose of the test is to effectively evaluate the matching of the internal mechanical interfaces of the connection and separation mechanism, its installation operability, unlocking and separation functions, and its compensation functions.

[0036] The core idea of ​​this invention is to use the ground separation test device for the bundled rocket booster of this invention to replace the side thruster rocket, full-size booster and core stage body, to simulate the real unlocking process and separation trajectory of the booster separation. Under the premise of effectively assessing the function of the connection and separation mechanism, the complexity and test cost of the booster ground separation test are greatly reduced.

[0037] Figure 1 The diagram shown is a schematic diagram of the ground separation test device for a bundled rocket booster according to an embodiment of the present invention. Figure 2 The diagram shown is a schematic representation of the connection between the wire rope and the booster simulator in an embodiment of the present invention.

[0038] See Figure 1 The ground separation test device for the rocket booster in this embodiment includes a booster simulation cabin 1, a first steel wire rope 2, a second steel wire rope 3, a gantry frame 4, a load-bearing wall 5, a steel wire rope fixing fixture 8, and a buffer device 9.

[0039] The load-bearing wall 5 is used to replace the core stage cabin; the booster simulation cabin 1 is modified from an existing launch vehicle cabin (such as a riveted cabin test piece), and the installation interfaces of the front connection separation mechanism 6 and the rear connection separation mechanism 7, as well as the connection interfaces of the first steel wire rope 2 and the second steel wire rope 3 are added to the existing launch vehicle cabin; both the load-bearing wall 5 and the steel wire rope fixing fixture 8 are steel ground test fixtures, and the load-bearing wall 5 is equipped with the installation interfaces of the front connection separation mechanism 6 and the rear connection separation mechanism 7; the buffer device 9 is a flexible body (such as sponge) that can withstand impact.

[0040] The gantry 4 is located above the booster simulation cabin 1; the wire rope fixing fixture 8 and the buffer device 9 are both located on one side of the booster simulation cabin 1 (in the direction of the separation and swing of the booster simulation cabin 1), and the buffer device 9 is between the booster simulation cabin 1 and the wire rope fixing fixture 8; the load-bearing wall 5 is located on the other side of the booster simulation cabin 1.

[0041] One end of the first wire rope 2 is connected to the first connection interface 102 on the bulkhead of the booster simulation cabin 1, and the other end of the first wire rope 2 is connected to the gantry 4; one end of the second wire rope 3 is connected to the second connection interface 103 on the bulkhead of the booster simulation cabin 1, and the other end of the second wire rope 3 is connected to the wire rope fixing fixture 8; the first wire rope 2 is equipped with a first tension control device 201, which controls the tension F1 of the first wire rope 2; the second wire rope 3 is equipped with a second tension control device 301, which controls the tension F2 of the second wire rope 3. Figure 2The booster simulator hull 1 has two first connection ports 102 and two second connection ports 103 on its bulkhead. The two first connection ports 102 are located at the same height, i.e., on the same diameter. The two second connection ports 103 are also located at the same height, i.e., on the same diameter, and the second connection ports 103 are at the same height as the center of mass 101 of the booster simulator hull 1, i.e., on the diameter passing through the center of mass 101 of the booster simulator hull 1. The distance between the first connection ports 102 and the second connection ports 103 is H. Figure 2 The booster simulator 1 is connected to the gantry 4 by two first steel wire ropes 2, and the booster simulator 1 is connected to the steel wire rope fixing fixture 8 by two second steel wire ropes 3.

[0042] The booster simulation chamber 1 is connected to the load-bearing wall 5 via a front connection separation mechanism 6 and a rear connection separation mechanism 7. These two mechanisms are the objects to be tested in the ground separation test. By adjusting the relative positions of the installation interfaces of the connection separation mechanisms on the booster simulation chamber 1 and the load-bearing wall 5, as well as the attitude of the booster simulation chamber 1, the structural displacement compensation capabilities of the front connection separation mechanism 6 and the rear connection separation mechanism 7 in the radial, axial, and tangential directions can be assessed.

[0043] The ground separation test method for the bundled rocket booster in this embodiment includes:

[0044] 1) Determine the relevant design parameters (F1, F2, θ, β, H) of the ground separation test device for the rocket booster to ensure that the separation attitude of the booster simulation compartment 1 is consistent with the design attitude of the booster's horizontal thrust rotation separation.

[0045] Based on the design of a new type of solid-propellant launch vehicle booster's lateral thrust-rotation separation attitude (the lateral thrust-rotation separation attitude includes rotational angular acceleration α, lateral acceleration a, and relative axial acceleration a1), and the calculation formula 1) 2F1·Sinθ·H=J z ·α;2)2F2·Cosβ+2F1·Sinθ=m·a;3)2F2·Sinβ+m·g-2F1·Cosθ=m·a1 Calculate the relevant design parameters (F1, F2, θ, β, H), where θ is the angle between the first wire rope 2 and the axis of the booster simulation cabin 1, β is the angle between the second wire rope 3 and the horizontal direction, m is the mass of the booster simulation cabin 1, F1 is the tension of the first wire rope 2, F2 is the tension of the second wire rope 3, J zLet be the moment of inertia of the booster simulation capsule 1 about its center of mass transverse axis; wherein, Equations 1) and 2) ensure that the booster simulation capsule 1 has the same rotational angular acceleration α and lateral acceleration a at the moment of unlocking as at the moment of actual separation of the booster, and let be the relative axial acceleration a1 between the booster and the core stage at the moment of separation, which must satisfy Equation 3).

[0046] The angle between the two first steel wire ropes 2 and the axis of the booster simulated cabin 1 is θ, and the tension of the two first steel wire ropes 2 is F1; the angle between the two second steel wire ropes 3 and the horizontal direction is β, and the tension of the two second steel wire ropes 3 is F2.

[0047] 2) Arrange the ground separation test device for the rocket booster based on the calculated relevant design parameters (F1, F2, θ, β, H);

[0048] The booster simulation cabin 1 is connected to the load-bearing wall 5 via the front connection separation mechanism 6 and the rear connection separation mechanism 7.

[0049] The booster simulation cabin 1 is connected to the gantry 4 via two first steel wire ropes 2. The angle between the first steel wire rope 2 and the axis of the booster simulation cabin 1 is θ. The tension of the first steel wire rope 2 is controlled to be F1 by the first tension control device 201. The booster simulation cabin 1 is connected to the steel wire rope fixing fixture 8 via two second steel wire ropes 3. The angle between the second steel wire rope 3 and the horizontal direction is β. The tension of the second steel wire rope 3 is controlled to be F2 by the second tension control device 301.

[0050] A buffer device 9 is placed in the direction of the separation swing of the booster simulation chamber 1. The distance L between the buffer device 9 and the booster simulation chamber 1 is consistent with the distance L between the axis of the booster simulation chamber 1 and the installation point of the first steel wire rope 2 on the gantry 4, so as to ensure that the swing kinetic energy of the booster simulation chamber 1 after unlocking is absorbed by the buffer device 9, and to ensure the safety of the test.

[0051] The distance M between the bottom of the booster simulation cabin 1 and the ground should ensure that the booster simulation cabin 1 does not collide with the ground during the swinging process after unlocking;

[0052] 3) Connect the power supply and test cables of the front connection separation mechanism 6 and the rear connection separation mechanism 7, and complete the preparation of auxiliary equipment such as testing and high-speed photography;

[0053] 4) After the unlocking command is issued, the front connection separation mechanism 6 and the rear connection separation mechanism 7 are unlocked, and the booster simulates the cabin 1 to be pushed and rotated out in the designed attitude.

[0054] 5) Observe, collect and analyze the status and test data of the front connection separation mechanism 6 and the rear connection separation mechanism 7 after unlocking, and complete the ground separation test.

[0055] When the design parameters of the launch vehicle separation attitude are adjusted, the relevant design parameters (F1, F2, θ, β, H, m) of this test device can be adjusted accordingly to ensure the effectiveness of this test method.

[0056] Obviously, those skilled in the art can make various modifications and variations to this invention without departing from its spirit and scope. Therefore, if these modifications and variations fall within the scope of the claims and their equivalents, this invention also intends to include these modifications and variations.

Claims

1. A ground separation test device for a strapped rocket booster, characterized in that, Includes booster simulator, first wire rope, second wire rope, gantry, load-bearing wall, wire rope fixing fixtures and buffer device; The load-bearing wall is used to replace the core stage cabin; the booster simulation cabin is obtained by modifying an existing launch vehicle cabin. The booster simulator is connected to the gantry via the first steel wire rope; The booster simulator is connected to the wire rope fixing fixture via a second wire rope. The booster simulator is connected to the load-bearing wall via a separation mechanism; The buffer device is located in the direction of the booster's simulated cabin separation and swing. The arrangement of the ground separation test device satisfies the following conditions: 1) 2F1·Sinθ·H =Jz·α 2) 2F2·Cosβ+2F1·Sinθ=m·a 3) 2F2·Sinβ+m·g-2F1·Cosθ=m·a1 Where θ is the angle between the first wire rope and the axis of the booster simulated cabin, β is the angle between the second wire rope and the horizontal direction, m is the mass of the booster simulated cabin, F1 is the tension of the first wire rope, F2 is the tension of the second wire rope, Jz is the moment of inertia of the booster simulated cabin about its center of mass horizontal axis, α is the rotational angular acceleration when the booster is unlocked and separated, a is the lateral acceleration when the booster is unlocked and separated, a1 is the relative axial acceleration when the booster is unlocked and separated; H is the distance between the connection point of the first wire rope and the booster simulated cabin and the connection point of the second wire rope and the booster simulated cabin.

2. The ground separation test device for a strapped rocket booster as described in claim 1, characterized in that, The connection point of the second wire rope to the booster simulator is at the same height as the center of mass of the booster simulator; the distance between the connection point of the first wire rope to the booster simulator and the connection point of the second wire rope to the booster simulator is H, and the connection point of the first wire rope to the booster simulator is located above the connection point of the second wire rope to the booster simulator.

3. The ground separation test device for a strapped rocket booster as described in claim 2, characterized in that, There are two first steel wire ropes, and the connection points of the two first steel wire ropes to the booster simulator are on the same diameter; there are two second steel wire ropes, and the connection points of the two second steel wire ropes to the booster simulator are on the same diameter.

4. The ground separation test device for a strapped rocket booster as described in claim 3, characterized in that, Each first wire rope is equipped with a first tension control device, which controls the tension so that the tension of the two first wire ropes is the same; each second wire rope is equipped with a second tension control device, which controls the tension so that the tension of the two second wire ropes is the same.

5. The ground separation test device for a strapped rocket booster as described in claim 1, characterized in that, The distance between the buffer device and the booster simulation cabin is L, and the distance between the axis of the booster simulation cabin and the installation point of the first wire rope on the gantry is L.

6. A ground separation test method for a strapped rocket booster, characterized in that, Using a ground separation test apparatus for a strapped rocket booster as described in any one of claims 1 to 4, the ground separation test method includes: 1) Based on the horizontal thrust rotation separation attitude of the bundled launch vehicle booster design, and the calculation formulas 1) 2F1·Sinθ·H=Jz·α; 2) 2F2·Cosβ+2F1·Sinθ=m·a; 3) 2F2·Sinβ+m·g-2F1·Cosθ=m·a1, calculate the relevant design parameters F1, F2, θ, β, and H, where θ is the angle between the first wire rope and the axis of the booster simulated cabin, β is the angle between the second wire rope and the horizontal direction, m is the mass of the booster simulated cabin, F1 is the tension of the first wire rope, F2 is the tension of the second wire rope, Jz is the moment of inertia of the booster simulated cabin about its center of mass horizontal axis, and H is the distance between the connection point of the first wire rope and the booster simulated cabin and the connection point of the second wire rope and the booster simulated cabin. 2) Arrange the ground separation test device for the bundled rocket boosters according to the relevant design parameters obtained from the calculation; 3) Connect the power supply and test cables of the front connection separation mechanism and the rear connection separation mechanism, and complete the preparation of test and auxiliary equipment; 4) After the unlocking command is issued, the front connection separation mechanism and the rear connection separation mechanism are unlocked, and the booster simulates the cabin to separate and swing out in the designed attitude. 5) Observe, collect and analyze the status and test data of the front and rear connection separation mechanisms after unlocking, and complete the ground separation test.

7. The ground separation test method for a bundled rocket booster as described in claim 6, characterized in that, Step 2) includes: The booster simulation chamber is connected to the load-bearing wall via a front connection separation mechanism and a rear connection separation mechanism. The booster simulator is connected to the gantry via two first steel wire ropes. The angle between the first steel wire rope and the axis of the booster simulator is θ. The tension of the first steel wire rope is controlled to be F1 by a first tension control device. The booster simulator is connected to the steel wire rope fixing fixture via two second steel wire ropes. The angle between the second steel wire rope and the horizontal direction is β. The tension of the second steel wire rope is controlled to be F2 by a second tension control device. A buffer device is placed in the direction of the simulated cabin separation swing of the booster.

8. The ground separation test method for a strapped rocket booster as described in claim 7, characterized in that, The distance L between the buffer device and the booster simulation cabin should be consistent with the distance L between the axis of the booster simulation cabin and the installation point of the first wire rope on the gantry; the distance M between the bottom of the booster simulation cabin and the ground should ensure that the booster simulation cabin does not collide with the ground during the swinging process after unlocking.

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