A CTS test system and method for large off-axis maneuvering separation

Abstract

This invention discloses a large off-axis maneuvering separation CTS test system. The front / rear end of the strain balance is connected to the belly support assembly, which is connected to a six-degree-of-freedom motion mechanism via a rolling motion mechanism. One end of the L-shaped front belly support rod of the belly support assembly is detachably connected to a connecting section, and the connecting section is detachably connected to the rear belly support rod. The other end of the L-shaped front belly support rod extends into the belly of the suspended object model and is connected to the front / rear end of the strain balance. The rear belly support rod is connected to the six-degree-of-freedom motion mechanism via a rolling motion mechanism. By changing and adjusting the connecting section, the CTS test system can be configured as a belly support system without pre-biasing and a belly support system with pre-biasing. The belly support system without pre-biasing is used for CTS tests in the angle-of-attack range of 0° to -60° or -120° to -180°. In the belly support system with pre-biasing, the suspended object model is first set to a pre-biased angle of attack during the CTS test, and the belly support system with pre-biasing is used for CTS tests in the angle-of-attack range of -60° to -120°. This invention provides a test method for capturing the separation trajectory of a suspended object during large off-axis maneuvers from 0 to -180°.

Description

Technical Field

[0001] This invention belongs to the field of experimental aerodynamics technology, and specifically relates to a CTS test system and method for large off-axis maneuver separation. Background Technology

[0002] Currently, omnidirectional launch capability is the trend and direction of the development of next-generation air-launched suspended objects (SPOs). This requires SPOs to possess post-stall over-the-shoulder launch technology, i.e., the ability to make rapid turns. Omnidirectional launch technology based on off-axis launch allows the carrier aircraft to launch SPOs at any angle within a 360° radius around the target. However, this omnidirectional launch is target-centric, requiring the target to be in front of the aircraft during launch. The advent of over-the-shoulder launch frees the carrier aircraft from this limitation, enabling control over the launch of the SPOs to be projected into any position within a 360° radius around the aircraft, thus achieving true omnidirectional launch.

[0003] Trajectory acquisition wind tunnel testing technology, as an advanced multi-body separation ground simulation technology, organically combines wind tunnel model testing with flight mechanics. Its outstanding advantages include high predictive accuracy, obtaining test results that are essentially consistent with full-scale flight test data. It can simulate complex separation conditions (such as launch assist force and the thrust of the external stores themselves) and special flight states (such as pitch, climb, or acceleration) in tests using computer software, adapting to launches under certain flight envelope conditions of the aircraft. It can directly provide the external store separation trajectory during testing, promptly evaluate separation characteristics, and modify relevant parameters as needed. The test not only obtains full-scale conditional separation trajectories but also directly measures the aerodynamic loads of the external stores at various measurement points along the separation trajectory, which is beneficial for the analysis and improvement of external store separation characteristics. Therefore, trajectory acquisition testing is a necessary type of wind tunnel test before the finalization of an air-launched weapon model.

[0004] Limited by the movement capabilities and operating space of the mechanism itself, existing trajectory capture wind tunnel test methods, which rely on relay technology, can usually only achieve movement with an angle of attack of no more than 90°. They do not have the test simulation capability of 0 to 180° and cannot meet the test requirements of large off-axis maneuvering launch after the suspension is separated. Therefore, it is urgent to develop corresponding simulation capabilities to broaden the scope of application of such test technologies. This invention is proposed in this practical context. Summary of the Invention

[0005] The purpose of this invention is to provide a CTS (Continuous Trajectory Switch) test system and method for large off-axis maneuver separation. This invention enables the capture test method of the separation trajectory of a suspended object with a large off-axis maneuver of 0 to -180°.

[0006] The technical solution of this invention: A large off-axis kinematic separation CTS test system includes a suspended model, inside which is a strain balance. The front and rear ends of the strain balance are connected to a belly support assembly, which is connected to a six-degree-of-freedom motion mechanism via a rolling motion mechanism. The belly support assembly includes an L-shaped front belly support rod, one end of which is detachably connected to a connecting section, and the connecting section is detachably connected to a rear belly support rod. The other end of the L-shaped front belly support rod extends into the belly of the suspended model and is connected to the front and rear ends of the strain balance. The rear belly support rod is connected to a six-degree-of-freedom motion mechanism via a rolling motion mechanism. The free-degree motion mechanism is connected; by changing and adjusting the connecting sections, the CTS test system can be configured into a system with and without pre-biased web support. The system without pre-biased web support is used for CTS tests in the angle-of-attack range of 0° to -60° or -120° to -180°. In the system with pre-biased web support, during the CTS test, the suspended model is first set with a pre-biased angle of attack, which is any angle within 0 to -180°. The system with pre-biased web support is used for CTS tests in the angle-of-attack range of -60° to -120°. The pre-biased angle of attack is the angle between the suspended model and the horizontal plane.

[0007] In the aforementioned CTS test system for large off-axis maneuver separation, the system without pre-biased bracing is tested in the CTS test range of 0° to -60° angle of attack, with the L-shaped bracing front rod connected to the rear end of the strain balance; the system with pre-biased bracing is tested in the CTS test range of -60° to -90° angle of attack, with the L-shaped bracing front rod connected to the rear end of the strain balance; the system with pre-biased bracing is tested in the CTS test range of -90° to -120° angle of attack, with the L-shaped bracing front rod connected to the front end of the strain balance; and the system without pre-biased bracing is tested in the CTS test range of -120° to -180° angle of attack, with the L-shaped bracing front rod connected to the front end of the strain balance.

[0008] In the aforementioned CTS test system for large off-axis maneuver separation, the horizontal cross-section of the support rod connecting the L-shaped front strut to the suspension model is an aerodynamic surface.

[0009] In the aforementioned CTS test system for large off-axis maneuver separation, the pre-angle of attack is within the angle of attack range of the CTS test.

[0010] In the aforementioned CTS test system for large off-axis maneuver separation, the pre-angle of attack is the midpoint of the angle of attack range for CTS testing.

[0011] The test method for the aforementioned CTS test system for large off-axis maneuver separation includes the following steps:

[0012] S1. Construct a CTS test system based on requirements;

[0013] S2. Construct a numerical simulation correction database for the suspended model with Mach number, angle of attack, and sideslip angle as variables, and obtain the corrected aerodynamic quantities;

[0014] S3. The six-degree-of-freedom motion mechanism moves the suspended model in the CTS test system to its initial position and initial attitude;

[0015] S4. Obtain the aerodynamic forces and aerodynamic moments of the suspended model at the initial time t0 using a strain balance, and correct them according to the corrected aerodynamic quantities in the numerical simulation database.

[0016] S5. Based on the aerodynamic forces, aerodynamic torques, flow field parameters, and preset suspension parameters of the suspended model at time t0, the six-degree-of-freedom motion equations are solved to obtain the attitude angle and position of the suspended model at the next time t1. The attitude angle and position of the suspended model at time t1 in the wind tunnel are obtained through the scaling relationship calculated using the preset suspension parameters. The six-degree-of-freedom motion mechanism adjusts the suspended model in the wind tunnel to the attitude angle and position at time t1. Then, based on the aerodynamic forces, aerodynamic torques, flow field parameters, and preset suspension parameters at time t1, the attitude angle and position of the suspended model in the wind tunnel at time t2 are calculated. This process is repeated until the end of the large off-axis maneuver separation phase of the suspended model at time t. n When the simulation time or simulation trip reaches the termination value.

[0017] In the aforementioned method of using the CTS test system for large off-axis maneuver separation, the airflow parameters of the flow field include wind tunnel dynamic pressure, static pressure, and Mach number.

[0018] In the aforementioned method of using the CTS test system for large off-axis maneuver separation, the preset suspension parameters include the reference length and reference area of ​​the actual suspension, as well as the reference length and reference area of ​​the suspension model.

[0019] In the aforementioned method of using the CTS test system for large off-axis maneuver separation, step 2 involves constructing the numerical simulation correction database as follows: Numerical simulations are conducted on individual suspension models and the connection configuration between the ventral support assembly and the suspension model under preset test aerodynamic parameter ranges, angle of attack ranges from 0 to -180°, and sideslip angle ranges from -10° to 10°. Based on the aerodynamic quantities obtained from the simulations and the aerodynamic quantities of the connection configuration measured, corrected aerodynamic quantities are calculated. Through parameter tuning, an optimizable Gaussian regression method is used to interpolate the corrected aerodynamic quantities under the corresponding Mach number, angle of attack, and sideslip angle conditions, extracting the corresponding aerodynamic correction data, and constructing the numerical simulation correction database.

[0020] In the aforementioned method of using the CTS test system for large off-axis maneuver separation, in step 2, the corrected aerodynamic quantity A... R Calculate using the following formula:

[0021] A R =A0+(A2-A1)

[0022] In the formula, A0 is the aerodynamic quantity of the connection configuration obtained by measurement, A1 is the aerodynamic quantity of the connection configuration obtained by numerical simulation, and A2 is the aerodynamic quantity of the individual suspended object model obtained by numerical simulation.

[0023] The beneficial effects of this invention are:

[0024] 1. This invention provides a capture test method for realizing the large off-axis maneuver separation trajectory of a suspended object from 0 to -180° in a wind tunnel. It can realize the wind tunnel simulation of the large off-axis maneuver launch process of the suspended object in the capture trajectory wind tunnel test through a relay method, and proposes a method and specific measures to correct the model shape damage and support interference caused by the belly support.

[0025] 2. Wind tunnel tests were conducted using the capture trajectory method of this invention to obtain the trajectory and attitude angle changes of the suspended object during the large off-axis maneuver separation process relative to the aircraft, and to determine the safety of the separation. This invention has the advantage of minimal disturbance during the simulation of the large off-axis maneuver separation process of the suspended object. Furthermore, this invention developed a CTS (Catch Trajectory Test) system for the separation of suspended objects during large off-axis maneuvers and established a novel correction method.

[0026] 3. This invention can achieve changes in the angle of attack of the suspended model within the range of 0 to -180° in wind tunnel trajectory capture tests, obtain the trajectory and attitude angle changes of the entire roll maneuver, greatly expand the test capability, obtain more complete test data, and develop a numerical correction method to correct the support interference of the belly support model, ensuring the reliability and accuracy of the test results. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of the trajectory capture CTS test of the present invention;

[0028] Figure 2 This is a schematic diagram showing the connection between the pre-biased bracing system of the present invention and the rear end of the strain balance;

[0029] Figure 3 This is a schematic diagram showing the connection between the pre-eccentric bracing system of the present invention and the rear end of the strain balance;

[0030] Figure 4 This is a schematic diagram showing the connection between the pre-biased bracing system of the present invention and the front end of the strain balance;

[0031] Figure 5 This is a schematic diagram showing the connection between the pre-eccentric support system and the front end of the strain balance of the present invention. Detailed Implementation

[0032] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0033] Example 1. A CTS test system for large off-axis maneuver separation, see [link to example]. Figures 1-5 The system includes a suspended model 1, inside which is a strain balance 2. The front and rear ends of the strain balance 2 are connected to a ventral support assembly 3. The ventral support assembly 3 is connected to a six-degree-of-freedom motion mechanism 5 via a rolling motion mechanism 4. The ventral support assembly 3 includes an L-shaped ventral support front rod 31. One end of the L-shaped ventral support front rod 31 is detachably connected to a connecting section 32, and the connecting section 32 is detachably connected to a ventral support rear rod 33. The other end of the L-shaped ventral support front rod 31 extends into the abdomen of the suspended model 1 and is connected to the front and rear ends of the strain balance 2. The ventral support rear rod 33 is connected to a six-degree-of-freedom motion mechanism 5 via the rolling motion mechanism 4. The motion mechanism 5 is connected; the CTS test system can be configured as a system without pre-biased bracing and a system with pre-biased bracing by changing and adjusting the connecting section 32; the system without pre-biased bracing is used for CTS tests in the angle of attack range of 0° to -60° or -120° to -180°; in the system with pre-biased bracing, during the CTS test, the suspended model 1 is first set with a pre-biased angle of attack, which is any angle within 0 to -180°, and the system with pre-biased bracing is used for CTS tests in the angle of attack range of -60° to -120°; the pre-biased angle of attack is the angle between the suspended model 1 and the horizontal plane.

[0034] Strain balance 2 is used to measure the aerodynamic forces acting on suspended model 1 during the experiment, providing the uncorrected aerodynamic input to the trajectory capture and calculation program.

[0035] In the non-pre-biased bracing system, the axis of the rear bracing rod 33 is parallel to the axis of the suspended model 1;

[0036] In the aforementioned CTS test of the non-pre-biased bracing system within the angle of attack range of 0° to -60°, the L-shaped bracing front rod 31 is connected to the rear end of the strain balance 2; in the CTS test of the pre-biased bracing system within the angle of attack range of -60° to -90°, the L-shaped bracing front rod 31 is connected to the rear end of the strain balance 2; in the CTS test of the pre-biased bracing system within the angle of attack range of -90° to -120°, the L-shaped bracing front rod 31 is connected to the front end of the strain balance 2; and in the CTS test of the non-pre-biased bracing system within the angle of attack range of -120° to -180°, the L-shaped bracing front rod 31 is connected to the front end of the strain balance 2.

[0037] The horizontal cross section of the support rod connecting the aforementioned L-shaped front strut 31 and the suspended model 1 is an aerodynamic surface to reduce support interference.

[0038] The aforementioned pre-angle of attack is within the angle of attack range of the CTS test.

[0039] Preferably, the aforementioned pre-angle of attack is the median value of the angle of attack range in the CTS test.

[0040] The test method for the aforementioned CTS test system for large off-axis maneuver separation includes the following steps:

[0041] S1. Construct a CTS test system based on requirements;

[0042] S2. Construct a numerical simulation correction database for suspended model 1 with Mach number, angle of attack, and sideslip angle as variables, and obtain the corrected aerodynamic quantities;

[0043] S3. The six-degree-of-freedom motion mechanism 5 moves the suspended model 1 in the CTS test system to its initial position and initial attitude;

[0044] S4. Obtain the aerodynamic forces and aerodynamic moments of the suspended model 1 at the initial time t0 using strain balance 2, and correct them according to the corrected aerodynamic quantities in the numerical simulation database; to avoid support interference from the belly support assembly 3.

[0045] S5. Based on the aerodynamic forces, aerodynamic torques, flow field parameters, and preset suspension parameters of suspended model 1 at time t0, the six-degree-of-freedom motion equations are solved to obtain the attitude angle and position of suspended model 1 at the next time t1. The attitude angle and position of suspended model 1 at time t1 are obtained in the wind tunnel through the scaling relationship calculated using the preset suspension parameters. The six-degree-of-freedom motion mechanism 5 adjusts suspended model 1 in the wind tunnel to the attitude angle and position at time t1. Then, based on the aerodynamic forces, aerodynamic torques, flow field parameters, and preset suspension parameters at time t1, the attitude angle and position of suspended model 1 in the wind tunnel at time t2 are calculated. This process is repeated until the end of the large off-axis maneuver separation phase of the suspended model at time t1. n When the simulation time or simulation trip reaches the termination value.

[0046] The aforementioned flow field parameters include wind tunnel dynamic pressure, static pressure, and Mach number.

[0047] The aforementioned preset suspension parameters include the reference length and reference area of ​​the actual suspension object, as well as the reference length and reference area of ​​the suspension object model.

[0048] In step 2 above, the numerical simulation correction database is constructed as follows: Numerical simulations are conducted on the individual suspension model 1, the connection configuration of the belly support assembly 3 and the suspension model 4 under preset test aerodynamic parameter ranges, angle of attack ranges from 0 to -180°, and sideslip angle ranges from -10° to 10°. Based on the aerodynamic quantities obtained from the simulation and the aerodynamic quantities of the connection configuration obtained from the measurement, the corrected aerodynamic quantities are calculated. By adjusting the parameters, an optimizable Gaussian regression method is used to interpolate the corrected aerodynamic quantities under the corresponding Mach number, angle of attack and sideslip angle conditions, extract the corresponding aerodynamic correction data, and construct the numerical simulation correction database.

[0049] In step 2 above, the aerodynamic quantity A is corrected. R Calculate using the following formula:

[0050] A R =A0+(A2-A1)

[0051] In the formula, A0 is the aerodynamic quantity of the connection configuration obtained by measurement, A1 is the aerodynamic quantity of the connection configuration obtained by numerical simulation, and A2 is the aerodynamic quantity of the individual suspended object model 1 obtained by numerical simulation.

[0052] For example: Under certain conditions, the aerodynamic quantity of the suspended model 4 connected to the head support mechanism is measured to be A0 in the experiment. At this time, the angle of the model under the local wind axis is (ɑ, β). Under the same conditions, through optimizable Gaussian interpolation, the aerodynamic quantity corresponding to the belly support disturbance at (ɑ, β) can be obtained from the numerical simulation correction database as A1. Under the same conditions, through optimizable Gaussian interpolation, the aerodynamic quantity corresponding to the clean suspended model at (ɑ, β) can be obtained from the numerical simulation correction database as A2. The corrected aerodynamic quantity A R =A0-(A2-A1). The corrected aerodynamic quantity A R The six-degree-of-freedom dynamic equations of the suspended object are input and solved to obtain its pose in the wind tunnel at the next moment. This method can correct the support disturbance caused by the ventral support assembly 3.

[0053] In this invention, the design must consider preventing interference with the openings of the suspended object model. By estimating the aerodynamic loads and corresponding elastic deformations on the model, the dimensions of the support rod and the opening form and size of the suspended object model at the position where the web connecting rod extends are determined. This ensures that the suspended object model does not collide with the web support rod throughout the test, while also minimizing damage to the original shape of the suspended object model.

[0054] In this invention, the number of segments and the specific segment angles within the angle of attack range are not limited. Specifically, within the angle of attack range of 0° to -45°, there is no connection between the pre-biased bracing system and the strain balance; within the angle of attack range of -45° to -135°, there is a pre-biased bracing system connected to the strain balance; and within the angle of attack range of -135° to -180°, there is no connection between the pre-biased bracing system and the strain balance. It is particularly important to note that the displacement and attitude angles of the model in the three directions at the relay point remain completely identical.

[0055] The above description is merely a specific embodiment of the present invention, providing a detailed description of the invention. Parts not covered herein are conventional techniques. However, the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention. The scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A CTS test system for large off-axis maneuver separation, characterized in that, The system includes a suspended model with a strain balance inside. The strain balance is connected to a ventral support assembly at its front and rear ends. This ventral support assembly is connected to a six-degree-of-freedom motion mechanism via a rolling motion mechanism. The ventral support assembly includes an L-shaped front ventral support rod. One end of the front ventral support rod is detachably connected to a connecting section, which is detachably connected to a rear ventral support rod. The other end of the L-shaped front ventral support rod extends into the abdomen of the suspended model and is connected to the front and rear ends of the strain balance. The rear ventral support rod is connected to a six-degree-of-freedom motion mechanism via a rolling motion mechanism. The system is connected via a series of interconnected mechanisms. The segment replacement and adjustment enable the CTS test system to be configured as a system with and without pre-biased bracing; the system without pre-biased bracing is used for CTS tests within the angle of attack range of 0° to -60° or -120° to -180°; in the system with pre-biased bracing, during CTS testing, the suspended model is first set with a pre-biased angle of attack, which can be any angle within 0° to -180°, and the system with pre-biased bracing is used for CTS tests within the angle of attack range of -60° to -120°; the pre-biased angle of attack is the angle between the suspended model and the horizontal plane; For the CTS test of the system without pre-eccentric bracing, the L-shaped bracing front rod is connected to the rear end of the strain balance within the angle of attack range of 0° to -60°; for the system with pre-eccentric bracing, the L-shaped bracing front rod is connected to the rear end of the strain balance within the angle of attack range of -60° to -90°; for the system with pre-eccentric bracing, the L-shaped bracing front rod is connected to the front end of the strain balance within the angle of attack range of -90° to -120°; and for the system without pre-eccentric bracing, the L-shaped bracing front rod is connected to the front end of the strain balance within the angle of attack range of -120° to -180°.

2. The CTS test system for large off-axis maneuver separation according to claim 1, characterized in that, The horizontal cross-section of the support rod connecting the L-shaped front strut to the suspended model is an aerodynamic surface.

3. The CTS test system for large off-axis maneuver separation according to claim 1, characterized in that, The pre-angle of attack is within the angle of attack range of the CTS test.

4. The CTS test system for large off-axis maneuver separation according to claim 3, characterized in that, The pre-angle of attack is the midpoint of the angle of attack range for CTS testing.

5. A method of using a CTS test system for large off-axis maneuver separation, comprising the CTS test system for large off-axis maneuver separation as described in any one of claims 1-4, characterized in that, Includes the following steps: S1. Construct a CTS test system based on requirements; S2. Construct a numerical simulation correction database for the suspended model with Mach number, angle of attack, and sideslip angle as variables, and obtain the corrected aerodynamic quantities; S3. The six-degree-of-freedom motion mechanism moves the suspended model in the CTS test system to its initial position and initial attitude; S4. Obtain the aerodynamic forces and aerodynamic moments of the suspended model at the initial time t0 using a strain balance, and correct them according to the corrected aerodynamic quantities in the numerical simulation database. S5. Based on the aerodynamic forces, aerodynamic torques, flow field parameters, and preset suspension parameters of the suspended model at time t0, the six-degree-of-freedom motion equations are solved to obtain the attitude angle and position of the suspended model at the next time t1. The attitude angle and position of the suspended model at time t1 in the wind tunnel are obtained through the scaling relationship calculated using the preset suspension parameters. The six-degree-of-freedom motion mechanism adjusts the suspended model in the wind tunnel to the attitude angle and position at time t1. Then, based on the aerodynamic forces, aerodynamic torques, flow field parameters, and preset suspension parameters at time t1, the attitude angle and position of the suspended model in the wind tunnel at time t2 are calculated. This process is repeated until the end of the large off-axis maneuver separation phase of the suspended model at time t. n When the simulation time or simulation trip reaches the termination value.

6. The method of using the CTS test system for large off-axis maneuver separation according to claim 5, characterized in that, The airflow parameters of the flow field include wind tunnel dynamic pressure, static pressure, and Mach number.

7. The method of using the CTS test system for large off-axis maneuver separation according to claim 5, characterized in that, The preset parameters for the suspended object include the reference length and reference area of ​​the actual suspended object, as well as the reference length and reference area of ​​the suspended object model.

8. The method of using the CTS test system for large off-axis maneuver separation according to claim 5, characterized in that, In step 2, the numerical simulation correction database is constructed as follows: Numerical simulations are conducted on individual suspension models and the connection configuration between the support assembly and the suspension model under preset test aerodynamic parameter ranges, angle of attack ranges from 0 to -180°, and sideslip angle ranges from -10° to 10°. Based on the aerodynamic quantities obtained from the simulation and the aerodynamic quantities of the connection configuration obtained from the measurement, the corrected aerodynamic quantities are calculated. Through parameter tuning, an optimizable Gaussian regression method is used to interpolate the corrected aerodynamic quantities under the corresponding Mach number, angle of attack, and sideslip angle conditions, extract the corresponding aerodynamic correction data, and construct the numerical simulation correction database.

9. The method of using the CTS test system for large off-axis maneuver separation according to claim 8, characterized in that, In step 2, the aerodynamic quantity A is corrected. R Calculate using the following formula: A R =A0+(A2-A1) In the formula, A0 is the aerodynamic quantity of the connection configuration obtained by measurement, A1 is the aerodynamic quantity of the connection configuration obtained by numerical simulation, and A2 is the aerodynamic quantity of the individual suspended object model obtained by numerical simulation.

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