Force measuring device and force measuring method for aircraft rocket sled test

Abstract

The invention relates to a force measuring device and a force measuring method for an aircraft rocket sled test, and belongs to the field of aerospace testing. The rocket sled body is horizontally arranged; the fixed supporting frame is vertically installed on the upper surface of the rocket sled body. The adapter bracket is fixedly mounted at the top of the fixed support frame; the diagonal draw bars are symmetrically arranged on the two sides of the fixed supporting frame. The top of the diagonal draw bar is connected with the side wall of the adapter bracket, and the bottom of the diagonal draw bar is connected with the upper surface of the rocket sled body; the instrument box is installed on the upper surface of the rocket sled body and located on the side wall of the fixed supporting frame. The aircraft model is mounted at the top of the adapter bracket; the balance assembly is arranged between the aircraft model and the adapter bracket; the aircraft model is in butt joint with the adapter bracket through the balance assembly. According to the invention, the full-size aerodynamic dynamic test of the aircraft is realized, and important ground test reference data is provided for aircraft development.

Description

Technical Field

[0001] This invention belongs to the field of aerospace testing and relates to a force measuring device and force measuring method for testing rocket sleds of aircraft. Background Technology

[0002] Rocket sled testing is a modern ground-based testing method that uses solid or liquid rocket engines to propel a rocket sled carrying test specimens and testing equipment at high speed along a dedicated track to achieve a predetermined Mach number, thereby obtaining the performance parameters of the test specimen. Rocket sled testing is a valuable supplement to wind tunnel and flight testing. Unlike wind tunnel testing, rocket sled testing can perform full-scale dynamic testing of test specimens without mass limitations, interference from tunnel walls and supports, and a wider range of test contents. Unlike flight testing, rocket sled testing is highly flexible, allows for repeatable testing processes, facilitates easier and more convenient data collection, and has lower testing costs. Rocket sled testing plays a crucial role in aerospace vehicle development, weaponry manufacturing, and high-tech testing, with test contents including ballistic simulation tests, ejection seat tests, parachute tests, flutter tests, impact damage tests, rain erosion tests, and ramjet engine ignition tests. However, among these numerous tests, aerodynamic research tests account for a relatively small proportion, and related literature reports are also relatively scarce. Summary of the Invention

[0003] The technical problem solved by this invention is to overcome the shortcomings of the prior art and propose a force measurement device and method for testing rocket sleds for aircraft, which realizes full-scale dynamic aerodynamic testing of aircraft and provides important ground test reference data for aircraft development.

[0004] The solution of the present invention is:

[0005] A force measuring device for testing rocket sleds for aircraft includes a balance assembly, a transfer bracket, a fixed support frame, a tie rod, an instrument box, a rocket sled body, and an aircraft model;

[0006] The rocket sled is placed horizontally; a fixed support frame is installed vertically on the upper surface of the rocket sled; an adapter bracket is fixedly installed on top of the fixed support frame; diagonal braces are symmetrically arranged on both sides of the fixed support frame; the top of the diagonal braces is connected to the side wall of the adapter bracket, and the bottom of the diagonal braces is connected to the upper surface of the rocket sled; an instrument box is installed on the upper surface of the rocket sled and located on the side wall of the fixed support frame; the aircraft model is installed horizontally on top of the adapter bracket; a balance assembly is set between the aircraft model and the adapter bracket; the aircraft model is connected to the adapter bracket through the balance assembly.

[0007] In the aforementioned test force measuring device for a rocket sled of an aircraft, the balance assembly includes a force measuring balance and two inertial modules;

[0008] The force balance is placed vertically; the top of the force balance extends upward into the inner cavity of the aircraft model; the bottom of the force balance is embedded downward into the groove of the adapter bracket; and two inertial modules are symmetrically installed at the axial ends of the top of the force balance.

[0009] In the aforementioned force measuring device for testing a rocket sled of an aircraft, the force measuring balance includes an elastic beam and a fixed end; wherein, the elastic beam is a column structure placed horizontally in the axial direction; the elastic beam is coaxially arranged in the inner cavity of the aircraft model; inertial modules are respectively installed at both ends of the elastic beam in the axial direction; the fixed end is a plate-like structure placed vertically in the axial direction; the fixed end is installed at the bottom of the elastic beam along the axis; the fixed end is connected to the adapter bracket.

[0010] In the aforementioned test force measuring device for a rocket sled of an aircraft, the instrument box contains data acquisition equipment and a power supply; the fixed support frame contains a cable tray, which allows the communication cable of the balance component to extend through the cable tray to the bottom of the fixed support frame and enter the instrument box from the bottom of the support frame to connect with the data acquisition equipment and the power supply.

[0011] In the aforementioned test force measuring device for a rocket sled of an aircraft, the angle between the upper and lower planes of the adapter bracket is θ; the value of θ ranges from 0° to 30°.

[0012] In the aforementioned test force measuring device for a rocket sled, the angle between the axis of the inclined rod and the plane of the rocket sled body is α, where α is less than 80°.

[0013] The force measurement method of the aforementioned test force measuring device for a rocket sled of an aircraft includes:

[0014] The entire force measuring device moves together along the track according to a predetermined plan. During the movement, the force balance measures the force F of the aircraft model; at the same time, the inertial module measures the acceleration a of the aircraft model.

[0015] Calculate the inertial force F of the aircraft model based on the acceleration a. 惯 ;

[0016] Based on the inertial force F of the aircraft model 惯 Calculate the aerodynamic force F of the aircraft model 气 .

[0017] In the above-mentioned force measurement method, the F 惯 The calculation method is as follows:

[0018] F 惯 =ma

[0019] In the formula, m is the mass of the aircraft model.

[0020] In the above-mentioned force measurement method, the aerodynamic force F 气The calculation method is as follows:

[0021] F 气 =FF 惯 .

[0022] In the aforementioned force measurement method, the vibration signal from the rocket sled's operation is included in the measurement information obtained by the force balance and inertial module. The measurement information is then filtered to remove the influence of vibration before the aerodynamic force F is measured. 气 The calculation.

[0023] The advantages of this invention compared to the prior art are:

[0024] (1) This invention provides a method for accurate measurement of aerodynamic forces of a real aircraft, which can perform full-size dynamic testing of the aircraft without being limited by mass, can be repeated, and has relatively low testing costs.

[0025] (2) Compared with wind tunnel testing equipment, the present invention is free from the interference of tunnel walls and supports, and the test data is closer to the real state;

[0026] (3) Compared with flight testing, this invention can be repeatedly verified, and the testing cost is relatively low. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of the overall force measuring device for the rocket sled test of the present invention;

[0028] Figure 2 This is a schematic cross-sectional view of the balance assembly of the present invention.

[0029] Figure 3 This is a schematic diagram of the force balance of the present invention;

[0030] Figure 4 This is a schematic diagram of the adapter bracket of the present invention. Detailed Implementation

[0031] The present invention will be further described below with reference to the embodiments.

[0032] This invention provides a force measurement device and method for testing rocket sleds for aircraft, enabling full-scale dynamic aerodynamic testing of aircraft and providing important ground test reference data for aircraft development.

[0033] Force measuring device for testing rocket sleds on aircraft, such as Figure 1As shown, the system specifically includes a balance assembly 1, an adapter bracket 2, a fixed support frame 3, a tie rod 4, an instrument case 5, a rocket sled body, and a spacecraft model. In this invention, the balance assembly 1 serves as the measurement unit of the entire device, comprising a force balance and an inertial module, used to sense force and motion information. The adapter bracket 2, acting as a connecting support, is located between the force balance and the fixed support frame; the angle between its upper and lower connecting surfaces needs to be machined according to the required angle of attack of the model during the experiment. The fixed support frame 3 serves as the overall support; its upper surface is used to fix the adapter bracket, and its lower surface is fixed to the rocket sled body. The instrument case 5 is mounted on the rocket sled body and contains built-in data acquisition equipment and a power supply.

[0034] The specific assembly is as follows: the rocket sled is placed horizontally; the fixed support frame 3 is vertically installed on the upper surface of the rocket sled; the adapter bracket 2 is fixedly installed on the top of the fixed support frame 3; the diagonal tie rods 4 are symmetrically arranged on both sides of the fixed support frame 3; the top of the diagonal tie rods 4 is connected to the side wall of the adapter bracket 2, and the bottom of the diagonal tie rods 4 is connected to the upper surface of the rocket sled; the instrument box 5 is installed on the upper surface of the rocket sled and located on the side wall of the fixed support frame 3; the aircraft model is horizontally installed on the top of the adapter bracket 2; the balance assembly 1 is located between the aircraft model and the adapter bracket 2; the aircraft model is connected to the adapter bracket 2 through the balance assembly 1. The instrument box 5 contains data acquisition equipment and a power supply; the fixed support frame 3 contains a cable tray, which allows the communication cable of the balance assembly 1 to extend through the cable tray to the bottom of the fixed support frame 3 and enter the instrument box 5 from the bottom of the support frame 3 to connect with the data acquisition equipment and the power supply.

[0035] The balance assembly 1 of this invention comprises two parts: a force balance and an inertial module. The force balance senses force information, and the inertial module senses motion information. The force balance does not have a fixed shape or structure, but can generally be divided into a fixed end, an elastic beam, and a measuring end. The inertial module is installed at the measuring end of the force balance, and can also be installed on an aircraft model.

[0036] like Figure 2 As shown, the balance assembly 1 specifically includes a force balance 11 and two inertial modules 12. The force balance 11 is placed vertically; the top of the force balance 11 extends upward into the inner cavity of the aircraft model; the bottom of the force balance 11 is embedded downward into the groove of the adapter bracket 2; the two inertial modules 12 are symmetrically installed at the axial ends of the top of the force balance 11.

[0037] like Figure 3 As shown, the force balance 11 includes an elastic beam and a fixed end; wherein, the elastic beam is a column structure placed horizontally in the axial direction; the elastic beam is coaxially arranged in the inner cavity of the aircraft model; inertial modules 12 are respectively installed at both ends of the elastic beam in the axial direction; the fixed end is a plate-shaped structure placed vertically in the axial direction; the fixed end is installed at the bottom of the elastic beam along the axis; the fixed end is connected to the adapter bracket 2.

[0038] The angle between the upper and lower planes of adapter bracket 2 is θ; the value of θ ranges from 0° to 30°. For example... Figure 4 The diagrams shown are for θ = 0° and 30° respectively. The adapter bracket 2 is fixed on the fixed support frame 3. The included angle between the upper and lower surfaces of the adapter bracket 2 needs to be machined according to the angle of attack requirements of the model during the test.

[0039] The angle between the axis of the diagonal tie rod 4 and the plane of the rocket sled is α, where α is less than 80°.

[0040] The fixed support frame 3, as an integral support, is welded from I-beams and plates. The upper end is used to fix the adapter bracket, and the lower end is fixed to the rocket skid body; its interior has a cable routing groove for threading wires.

[0041] The force measurement method based on the force measurement device for a rocket skid test of an aircraft specifically includes the following steps:

[0042] The entire force measuring device moves together along the track according to the predetermined plan. During the movement, the force measuring balance 11 measures the force F of the aircraft model; at the same time, the inertial module 12 measures the acceleration a of the aircraft model.

[0043] Calculate the inertial force F of the aircraft model based on the acceleration a. 惯 ;F 惯 The calculation method is as follows:

[0044] F 惯 =ma

[0045] In the formula, m is the mass of the aircraft model.

[0046] Based on the inertial force F of the aircraft model 惯 Calculate the aerodynamic force F of the aircraft model 气 Aerodynamic force F 气 The calculation method is as follows:

[0047] F 气 =FF 惯 .

[0048] The vibration signal from the rocket sled's operation is included in the measurement information obtained by the force balance 11 and the inertial module 12. The measurement information is filtered to remove the influence of vibration before the aerodynamic force F is measured. 气 The calculation.

[0049] The force information sensed by the force balance 11, including aerodynamic force and inertial force, needs to be corrected by the motion information sensed by the inertial module 12 to obtain the aerodynamic force of the aircraft model.

[0050] Example

[0051] This invention relates to a force measuring device and method for testing rocket sleds for aircraft, mainly comprising a balance assembly, a transfer bracket, a fixed support frame, a tie rod, and an instrument box. From top to bottom, the balance assembly, the transfer bracket, and the fixed support frame are connected in sequence. The fixed support frame and the instrument box are installed side by side on the rocket sled body. The two ends of the tie rod are respectively connected to the side of the transfer bracket and the rocket sled body.

[0052] The balance assembly consists of a force balance and an inertial module. The fixed end of the force balance is inserted into the through slot of the adapter bracket and fixed, while the measuring end is equipped with the inertial module and connected to the aircraft model.

[0053] The adapter bracket has its lower end fixed to a fixed support frame, and the included angle between the upper and lower surfaces is determined according to the requirements of the test mission. By changing the adapter bracket with different included angles, different angles of attack requirements for the aircraft model can be achieved.

[0054] The fixed support frame is welded from I-beams and sheet metal, and is narrow at the top and wide at the bottom. It serves as a stable support for the entire device and has a cable passage inside, which facilitates the routing of the balance component's cable into the instrument box.

[0055] The diagonal tie rod is fixed at one end to the side of the adapter bracket and at the other end to the rocket skid. The length of the diagonal tie rod can be finely adjusted, which facilitates installation and allows for the application of preload, thereby ensuring the lateral stability of the entire device.

[0056] The instrument case, with sloping front and back, is fixed to the rocket skid and contains data acquisition equipment and power supply. The cable runs out from the bottom of the fixed support frame and enters the instrument case to connect with the data acquisition equipment and power supply.

[0057] In this embodiment,

[0058] The force balance has a fixed end in the middle, which is inserted into the through slot of the adapter bracket and fixed in place. The two ends are two measuring ends: a first measuring end and a second measuring end. Both measuring ends are connected to the aircraft model to ensure the stability and safety of the aircraft support. Except for the two measuring ends, the rest of the force balance does not contact the aircraft model.

[0059] There are two adapter brackets, with the included angles of 0° and 16° between their upper and lower surfaces, respectively.

[0060] The angle between the axis of the diagonal tie rod and the upper surface of the rocket sled is 63°.

[0061] This invention provides a method for accurate measurement of the aerodynamic forces of a real aircraft, which can perform full-scale dynamic testing of the aircraft without being limited by mass, can be repeated, and has relatively low testing costs. Compared with wind tunnel testing equipment, this invention does not have the interference of tunnel walls and supports, and the test data is closer to the real state. Compared with flight testing, this invention can be repeatedly verified, and the testing cost is relatively low.

[0062] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention by utilizing the methods and techniques disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and alterations made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.

Claims

1. A force measuring device for testing rocket sleds on aircraft, characterized in that: Includes balance assembly (1), adapter bracket (2), fixed support frame (3), diagonal tie rod (4), instrument box (5), rocket sled body and aircraft model; Among them, the rocket sled body is placed horizontally; the fixed support frame (3) is installed vertically on the upper surface of the rocket sled body; the adapter bracket (2) is fixedly installed on the top of the fixed support frame (3); the diagonal tie rod (4) is symmetrically arranged on both sides of the fixed support frame (3); the top of the diagonal tie rod (4) is connected to the side wall of the adapter bracket (2), and the bottom of the diagonal tie rod (4) is connected to the upper surface of the rocket sled body; the instrument box (5) is installed on the upper surface of the rocket sled body and is located at the side wall of the fixed support frame (3); the aircraft model is installed horizontally on the top of the adapter bracket (2); the balance assembly (1) is set between the aircraft model and the adapter bracket (2); the aircraft model is connected to the adapter bracket (2) through the balance assembly (1).

2. The force measuring device for testing a rocket sled of an aircraft according to claim 1, characterized in that: The balance assembly (1) includes a force balance (11) and two inertial modules (12); Among them, the force balance (11) is placed vertically; the top of the force balance (11) extends upward into the inner cavity of the aircraft model; the bottom of the force balance (11) is embedded downward into the groove of the adapter bracket (2); two inertial modules (12) are symmetrically installed at both ends of the axial direction of the top of the force balance (11).

3. The force measuring device for testing a rocket sled of an aircraft according to claim 2, characterized in that: The force balance (11) includes an elastic beam and a fixed end; wherein, the elastic beam is a column structure placed horizontally in the axial direction; the elastic beam is coaxially arranged in the inner cavity of the aircraft model; inertial modules (12) are respectively installed at both ends of the elastic beam in the axial direction; the fixed end is a plate structure placed vertically in the axial direction; the fixed end is installed at the bottom of the elastic beam along the axis; the fixed end is connected to the adapter bracket (2).

4. The force measuring device for testing a rocket sled of an aircraft according to claim 1, characterized in that: The instrument box (5) is equipped with data acquisition equipment and power supply; the fixed support frame (3) is equipped with a cable tray, so that the communication line of the balance component (1) can be extended through the cable tray to the bottom of the fixed support frame (3) and enter the instrument box (5) from the bottom of the support frame (3) to connect with the data acquisition equipment and power supply.

5. The force measuring device for testing a rocket sled of an aircraft according to claim 1, characterized in that: The angle between the upper and lower planes of the adapter bracket (2) is θ; the value of θ ranges from 0° to 30°.

6. The force measuring device for testing a rocket sled of an aircraft according to claim 1, characterized in that: The angle between the axis of the diagonal tie rod (4) and the plane of the rocket sled is α, where α is less than 80°.

7. The force measurement method of the test force measuring device for a rocket sled of an aircraft according to claim 3, characterized in that: include: The entire force measuring device moves together along the track according to the predetermined plan. During the movement, the force measuring balance (11) measures the force F of the aircraft model; at the same time, the inertial module (12) measures the acceleration a of the aircraft model. Calculate the inertial force F of the aircraft model based on the acceleration a. 惯 ; Based on the inertial force F of the aircraft model 惯 Calculate the aerodynamic force F of the aircraft model 气 .

8. The force measurement method according to claim 7, characterized in that: The F 惯 The calculation method is as follows: F 惯 =at In the formula, m is the mass of the aircraft model.

9. The force measurement method according to claim 7, characterized in that: The aerodynamic force F 气 The calculation method is as follows: F 气 =F-F 惯 。 10. The force measuring method according to claim 8, characterized in that: The vibration signal of the rocket sled during operation is included in the measurement information obtained by the force balance (11) and the inertial module (12). The measurement information is filtered to remove the influence of vibration before the aerodynamic force F is measured. 气 The calculation.

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