Inclined test method and system of aircraft interstage separation device

Abstract

The invention provides a test method and system for an aircraft interstage separation device. The test method comprises the steps that S1, the aircraft interstage separation device is installed on a special tool at the inclination angle of 45 degrees; s2, an ignition pulse is sent through a remote control system, a cutting rope is triggered to act, and the cutting rope cuts the cabin body under the action of the ignition pulse; s3, the separation spring pushes the interstage cabin to fly away after the cutting rope acts, and the whole process from separation to landing of the interstage cabin is recorded through a high-speed photographing device; and S4, calculating whether the separating force meets the design requirement or not according to the data recorded by the high-speed photographing device in combination with known physical parameters. And S5, the impact on the projectile body in the separation process is recorded through an impact sensor, and impact data is provided for full-projectile design. According to the invention, the performance of the separation device under different attitudes can be more comprehensively verified by testing under the deflection attitude, and the reliability of the test is improved.

Description

Technical Field

[0001] This invention relates to the field of aircraft testing technology, and more specifically, to a method for oblique placement testing of an interstage separation device for an aircraft. Background Technology

[0002] In the design and testing of aircraft, the performance verification of the interstage separation device is a crucial step in ensuring the reliability and safety of the aircraft. Traditional separation device testing methods are typically conducted under standard attitudes, i.e., the aircraft maintains a vertical or horizontal attitude. However, in actual flight, the aircraft may face various attitude changes, including yaw.

[0003] Therefore, a test method is needed to verify the performance of the separation device under skewed attitude in order to more comprehensively evaluate the reliability of the separation device under different operating conditions. Summary of the Invention

[0004] To address the shortcomings of existing technologies, the purpose of this invention is to provide a method and system for oblique testing of interstage separation devices for aircraft.

[0005] A test method for an interstage separation device for an aircraft according to the present invention includes the following steps:

[0006] Step S1: Install the interstage separation device of the aircraft at a 45-degree angle on the special tooling;

[0007] Step S2: Send an ignition pulse through the remote control system to trigger the cutting cable action. The cutting cable cuts the cabin under the action of the ignition pulse.

[0008] Step S3: After the separation spring moves, it propels the interstage capsule away. The entire process from separation to the landing of the interstage capsule is recorded by a high-speed camera.

[0009] Step S4: Using the data recorded by the high-speed photography device and the known physical parameters, calculate whether the separation force meets the design requirements.

[0010] Step S5: Record the impact of the separation process on the projectile using an impact sensor to provide impact data for the overall projectile design.

[0011] Preferably, in step S1, a circuit continuity check is performed after the inter-stage separation device of the aircraft is installed.

[0012] Preferably, the remote control system adopts a redundant design, including a main system and a backup system, so that the backup system can take over when the main system fails.

[0013] Preferably, an impact sensor is installed on the tail section of the main stage of the aircraft to record the impact data of the missile body during the separation process.

[0014] Preferably, the formula for calculating the separation force in step S4 is as follows.

[0015] Vx = L / t

[0016]

[0017] F = mV 2 / x

[0018] Where: Vx is the horizontal flight velocity at the moment of separation; L is the horizontal flight distance; t is the time from ignition to the landing of the interstage capsule; Vy is the altitude flight velocity at the moment of separation; V is the combined velocity at separation; m is the mass of the interstage capsule; x is the compression of the separation spring; and F is the initial thrust provided by the separation spring.

[0019] Preferably, in step S2, a multi-level safety check mechanism is added before the ignition pulse is sent to ensure that the test conditions are fully met before ignition is triggered.

[0020] Preferably, the special tooling is equipped with multiple sensors for real-time monitoring of the force and attitude changes of the interstage separation device of the aircraft under skewed attitude.

[0021] Preferably, step S3 further includes: confirming the separation status through the observation hole, entering the site for observation after ensuring safety, confirming the separation status by observing the wreckage, and measuring the flight distance.

[0022] A test system for an interstage separation device of an aircraft according to the present invention includes:

[0023] Module M1: The interstage separation device of the aircraft is mounted at a 45-degree angle on a special tooling.

[0024] Module M2: Sends an ignition pulse through the remote control system to trigger the cutting cable action, and the cutting cable cuts the cabin under the action of the ignition pulse;

[0025] Module M3: The separation spring propels the interstage capsule away after the cutting cable is activated, and the entire process from separation to the landing of the interstage capsule is recorded by a high-speed camera.

[0026] Module M4: Calculates whether the separation force meets the design requirements by combining data recorded by a high-speed photography device with known physical parameters.

[0027] Compared with the prior art, the present invention has the following beneficial effects:

[0028] 1. Comprehensive performance verification: By conducting tests under skewed attitudes, the performance of the separation device under different attitudes can be more comprehensively verified, improving the reliability of the test.

[0029] 2. Improve safety: Remote control of ignition and high-speed photography recording process ensure the safety of test personnel and avoid misoperation during the test.

[0030] 3. Accurate assessment of separation force: Data recorded by high-speed photography equipment and calculation formulas can accurately assess whether the separation force meets the design requirements, improving the scientific nature and accuracy of the experiment.

[0031] 4. Optimize design: The test results can be used to optimize the design of the separation device, thereby improving the reliability and safety of the aircraft. Attached Figure Description

[0032] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0033] Figure 1 This is a flowchart of the experimental process of the present invention;

[0034] Figure 2 This is a diagram of the test setup;

[0035] Figure 3 The diagram shows the trajectory of the separated objects. In the diagram, H represents the flight distance in the vertical direction, and L represents the flight distance in the horizontal direction. Detailed Implementation

[0036] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0037] Example 1:

[0038] This invention discloses an oblique test method for an interstage separation device of an aircraft, referring to... Figure 1 As shown, it includes the following steps:

[0039] Step S1: Installation of the test apparatus;

[0040] ①According Figure 2 The test site was set up, and the interstage separation device of the aircraft was installed at a 45-degree angle on a special tooling to ensure that the device remained stable during the test.

[0041] ②The tooling should have sufficient strength and stability to withstand the forces generated during the separation process.

[0042] ③ After installation, a continuity check should be performed to ensure a reliable connection.

[0043] Step S2: Turn on the data detection device;

[0044] ① Turn on the impact sensor and start monitoring the impact sensor data.

[0045] ② Turn on the high-speed photography device to begin monitoring the separation process.

[0046] Step S3: Remote interstage separation control ignition;

[0047] ① An ignition pulse is sent through the remote control system to trigger the cutting cable action, and the cutting cable cuts the cabin under the action of the ignition pulse.

[0048] ② Ensure the safety and reliability of the remote control system to avoid misoperation during the test.

[0049] Step S4: Record the separation process;

[0050] ① After the separation spring actuates the cutting cable, it propels the interstage capsule away. The entire process from separation to the capsule's landing is recorded by a high-speed camera, and the separation impact is recorded by an impact sensor monitoring device. The trajectory after separation is as follows: Figure 3 As shown.

[0051] ② The high-speed photography device should have sufficient frame rate and resolution to clearly record the details of the separation process.

[0052] Step S5: On-site confirmation of separation results;

[0053] ① Confirm the separation status through the observation hole and enter the site for observation only after ensuring safety.

[0054] ② By observing the wreckage, confirm the separation and measure the flight distance.

[0055] Step S6: Calculate the separation force;

[0056] By analyzing the data recorded by the high-speed photography device, the flight time from ignition to landing is analyzed. Combined with known physical parameters and on-site measured flight distance, the following calculation formula is used to estimate whether the separation force meets the design requirements.

[0057] Vx = L / t

[0058]

[0059] F = mV 2 / x

[0060] Based on the measurement results L = 8.5m, H = 0.4m, m = 10kg, x = 0.016m, and the high-speed photography analysis data t = 1.34s, the following can be calculated:

[0061] Initial horizontal velocity Vx = 6.34 m / s

[0062] Initial vertical velocity Vy = 6.26 m / s

[0063] The resultant velocity V = 8.92 m / s

[0064] The separation force is F = 12722 N.

[0065] Example 2

[0066] Based on Example 1, the experimental method was further optimized to improve the accuracy and reliability of the experiment.

[0067] Optimization of experimental setup installation:

[0068] Multiple sensors were added to the tooling to monitor the force and attitude changes of the separation device in real time under skewed posture.

[0069] Optimized remote ignition control:

[0070] ① A redundant remote control system is adopted to ensure that the backup system can take over in time when the main system fails, thus avoiding test interruption.

[0071] ② Before the ignition pulse is sent, a multi-level safety check mechanism is added to ensure that the test conditions are fully met before ignition is triggered.

[0072] Separation process recording optimization:

[0073] ① Add multiple high-speed photography devices to record the separation process from different angles, ensuring the comprehensiveness and accuracy of the recorded data.

[0074] ② Employ multi-angle high-speed photography data fusion technology to improve the accuracy and reliability of the separation process recording.

[0075] The present invention also provides a test system for an interstage separation device of an aircraft. The test system for the interstage separation device of an aircraft can be implemented by executing the process steps of the test method for the interstage separation device of an aircraft. That is, those skilled in the art can understand the test method for the interstage separation device of an aircraft as a preferred embodiment of the test system for the interstage separation device of an aircraft.

[0076] This invention provides a test system for an interstage separation device for an aircraft, comprising:

[0077] Module M1: The interstage separation device of the aircraft is mounted at a 45-degree angle on a special tooling.

[0078] Module M2: Sends an ignition pulse through the remote control system to trigger the cutting cable action, and the cutting cable cuts the cabin under the action of the ignition pulse;

[0079] Module M3: The separation spring propels the interstage capsule away after the cutting cable is activated, and the entire process from separation to the landing of the interstage capsule is recorded by a high-speed camera.

[0080] Module M4: Calculates whether the separation force meets the design requirements by combining data recorded by a high-speed photography device with known physical parameters.

[0081] Those skilled in the art will understand that, besides implementing the system and its various devices, modules, and units provided by this invention in the form of purely computer-readable program code, the same functions can be achieved entirely through logical programming of the method steps, making the system and its various devices, modules, and units of this invention function in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers. Therefore, the system and its various devices, modules, and units provided by this invention can be considered as a hardware component, and the devices, modules, and units included therein for implementing various functions can also be considered as structures within the hardware component; alternatively, the devices, modules, and units for implementing various functions can be considered as both software modules implementing the method and structures within the hardware component.

[0082] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A test method for an interstage separation device for an aircraft, characterized in that, Includes the following steps: Step S1: Install the interstage separation device of the aircraft at a 45-degree angle on the special tooling; Step S2: Send an ignition pulse through the remote control system to trigger the cutting cable action. The cutting cable cuts the cabin under the action of the ignition pulse. Step S3: After the separation spring moves, it propels the interstage capsule away. The entire process from separation to the landing of the interstage capsule is recorded by a high-speed camera. Step S4: Using the data recorded by the high-speed photography device and the known physical parameters, calculate whether the separation force meets the design requirements. Step S5: Record the impact of the separation process on the projectile using an impact sensor to provide impact data for the overall projectile design.

2. The test method for the interstage separation device of a spacecraft according to claim 1, characterized in that, In step S1, after the inter-stage separation device of the aircraft is installed, a circuit continuity check is performed.

3. The test method for the interstage separation device of an aircraft according to claim 1, characterized in that, The remote control system adopts a redundant design, including a main system and a backup system. When the main system fails, the backup system can take over.

4. The test method for the interstage separation device of an aircraft according to claim 1, characterized in that, Impact sensors are installed on the tail section of the main stage of the aircraft to record the impact data on the missile body during the separation process.

5. The test method for the interstage separation device of an aircraft according to claim 1, characterized in that, The formula for calculating the separation force in step S4 is as follows. Vx = L / t F=mV 2 / x Where: Vx is the horizontal flight velocity at the moment of separation; L is the horizontal flight distance; t is the time from ignition to the landing of the interstage capsule; Vy is the altitude flight velocity at the moment of separation; V is the combined velocity at separation; m is the mass of the interstage capsule; x is the compression of the separation spring; and F is the initial thrust provided by the separation spring.

6. The test method for the interstage separation device of an aircraft according to claim 1, characterized in that, In step S2, a multi-level safety check mechanism is added before the ignition pulse is sent to ensure that the test conditions are fully met before ignition is triggered.

7. The test method for the interstage separation device of an aircraft according to claim 1, characterized in that, The special tooling is equipped with multiple sensors to monitor in real time the force and attitude changes of the interstage separation device of the aircraft under skewed attitude.

8. The test method for the interstage separation device of an aircraft according to claim 1, characterized in that, Step S3 further includes: confirming the separation status through the observation hole, entering the site for observation after ensuring safety, confirming the separation status by observing the wreckage, and measuring the flight distance.

9. A test system for an interstage separation device of an aircraft, characterized in that, include: Module M1: The interstage separation device of the aircraft is mounted at a 45-degree angle on a special tooling. Module M2: Sends an ignition pulse through the remote control system to trigger the cutting cable action, and the cutting cable cuts the cabin under the action of the ignition pulse; Module M3: The separation spring propels the interstage capsule away after the cutting cable is activated, and the entire process from separation to the landing of the interstage capsule is recorded by a high-speed camera. Module M4: Calculates whether the separation force meets the design requirements by combining data recorded by a high-speed photography device with known physical parameters.

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