Test evaluation device and method for pneumatic interference effect of attitude control jet flow in shape of slender body

Abstract

The invention belongs to the technical field of hypersonic wind tunnel tests, and discloses a test evaluation device and method for a slender body appearance attitude control jet flow aerodynamic interference effect. The test evaluation device comprises a spray pipe bracket, a sieve-shaped core pipe and a balance which are sequentially connected from front to back; the balance adopts an annular structure, a semiconductor strain gauge is pasted on a sensitive element of the balance, the rear end of the balance is connected with a jet-flow supporting rod, and the jet-flow supporting rod is provided with a jet-flow air inlet; a spray pipe is fixed on the spray pipe bracket; a spray pipe outlet penetrates out of the aircraft model; a jet flow pipeline which sequentially penetrates through the jet pipe support, the sieve-shaped core pipe, the aerodynamic force measuring balance and the jet flow supporting rod is arranged on the central axis of the aircraft model. The test evaluation method comprises the steps of conventional force measurement test, jet flow force measurement test, determination of influence quantity of jet flow interference, jet flow supplementary force measurement test, determination of jet flow medium parameters, and establishment of a jet flow state table of the attitude control jet flow engine of the slender aircraft. And technical support is provided for design and installation of the attitude control jet engine of the slender aircraft.

Description

Technical Field

[0001] The present invention belongs to the technical field of hypersonic wind tunnel tests, and in particular relates to a test and evaluation device and method for aerodynamic interference effects of an attitude-controlled jet with a slender body shape. Background Art

[0002] Modern aircraft, especially slender aircraft, have high requirements for maneuverability and agility. On the one hand, the aircraft is required to have a large extreme maneuvering overload capacity, and on the other hand, the aircraft is required to have a faster response speed to control commands. In response to the requirements of fast and large maneuvers, the use of attitude control jet engines is a more reasonable solution. Attitude control jet engines can provide additional control force or control torque to enhance the aircraft's extreme maneuvering overload capacity. In addition, the time required for attitude control jet engines to establish stable flow and provide additional thrust is relatively short, and the system response speed is fast, which can effectively meet the aircraft's rapid response requirements.

[0003] The airflow ejected by the attitude control jet engine will interfere with the air flow around the aircraft, thereby affecting the pressure distribution on the aircraft surface. The aerodynamic force acting on the aircraft in the state of jet flow will be different from that in the state of no jet flow, thus affecting the control effect of the attitude control jet engine. Because the jet interference flow is complex, different incoming flow conditions, different aircraft shapes, different nozzle arrangements, different nozzle thrusts and jet parameters will produce different interference situations. Sometimes the interference effect of the jet on the aerodynamic force will partially or even completely offset the effect of the nozzle thrust. It is necessary to test and evaluate the specific attitude control jet aerodynamic interference effect on the ground.

[0004] Currently, there is an urgent need to develop an experimental evaluation device and method for the aerodynamic interference effect of attitude control jets with slender body shapes. Summary of the invention

[0005] One technical problem to be solved by the present invention is to provide a test and evaluation device for the aerodynamic interference effect of an attitude control jet with a slender body shape. Another technical problem to be solved by the present invention is to provide a test and evaluation method for the aerodynamic interference effect of an attitude control jet with a slender body shape.

[0006] In the jet test, the aerodynamic force of the aircraft model is affected by the jet interference and undergoes significant changes. Ensuring the measurement accuracy and precision of the aerodynamic force measurement balance within a larger load measurement range is the key to ensuring the quality of the jet force measurement test data. At the same time, when conducting jet force measurement tests, especially thermal jet tests, because the working time of the thermal jet engine is often relatively short (about 100ms), the aerodynamic force measurement balance is required to have good dynamic response characteristics. The design of the jet balance is, in principle, the same as that of a conventional balance; but it has its own particularities compared to a conventional balance. On the one hand, the structure of the jet force measurement test device is complex, and is limited by the reduction ratio and the blockage degree of the wind tunnel jet test. The aircraft model is relatively small, and it is necessary to arrange the jet balance, nozzle, jet pipe and other necessary components in a limited space. The jet balance must be integrated with the aircraft model and the jet device, and a jet pipe needs to be set inside the jet balance along the central axis. On the other hand, the jet force measurement test requires that the jet balance not only has a high sensitivity, but also has a high frequency response characteristic. Therefore, sticking a semiconductor strain gauge with high strain sensitivity on the sensitive element of the jet balance can take into account both sensitivity and frequency response requirements.

[0007] The test and evaluation device for the aerodynamic interference effect of the attitude control jet of the slender body shape of the present invention comprises a nozzle bracket, a sieve core tube and an aerodynamic measurement balance which are located in the inner cavity of the aircraft model and are sequentially connected from front to back; the aerodynamic measurement balance adopts an annular structure, and a semiconductor strain gauge is attached to the sensitive element of the balance; the rear end of the aerodynamic measurement balance is connected to a jet support rod, and a jet air inlet is opened on the jet support rod; On the central axis of the aircraft model, a jet pipe is arranged which sequentially passes through the nozzle bracket, the sieve core tube, the aerodynamic measurement balance and the jet support rod, and the jet pipe is connected with the jet air inlet; A plurality of nozzles are fixed on the nozzle bracket, and each nozzle passes through the corresponding through hole on the aircraft model and out of the aircraft model. An annular gap is arranged between each nozzle outlet and the corresponding through hole, and each nozzle outlet has a smooth transition with the surface of the aircraft model.

[0008] Furthermore, a pressure monitoring hole is arranged on the sieve-like core tube for monitoring the pressure of the jet chamber and for adjusting the jet pressure of each nozzle chamber.

[0009] Furthermore, the aerodynamic force measurement balance is a ring-type six-component balance, the front section of which is provided with a parallelogram flexible assembly for measuring axial force, and the rear section is provided with a four-column beam measuring element for measuring normal force, lateral force, pitch moment, yaw moment and roll moment.

[0010] Furthermore, four varistors with equal resistance are arranged on the semiconductor strain gauge to form a Wheatstone bridge, so as to reduce the temperature effect and take into account the sensitivity and frequency response requirements of the aerodynamic measurement balance.

[0011] The test and evaluation method of the aerodynamic interference effect of the attitude control jet of the slender body shape of the present invention comprises the following steps: S10. Conduct conventional force measurement tests in hypersonic wind tunnels; Prepare a routine test schedule, follow the routine force test process of the hypersonic wind tunnel, change the sideslip angle, roll angle and angle of attack of the aircraft model in sequence, and complete the routine force test of the hypersonic wind tunnel; S20. Conduct hypersonic wind tunnel jet force measurement test; According to the flight state of the slender aircraft, the corresponding test state is selected in the conventional test plan table to carry out the jet force measurement test; during the jet force measurement test, the jet medium after pressure and temperature adjustment is introduced into the jet pipe through the jet air inlet and then ejected through the nozzle outlet to complete the hypersonic wind tunnel jet force measurement test; S30. Determine the impact amount of jet interference; The hypersonic wind tunnel jet force measurement test data and the conventional hypersonic wind tunnel force measurement test data were compared and analyzed to determine the influence of the jet interference. S40. Conduct supplementary force measurement test of hypersonic wind tunnel jet; Adjust the jet medium parameters and conduct supplementary force measurement tests on the hypersonic wind tunnel jet; S50. Determine the jet medium parameters taking into account the jet interference effect; Comparative analysis is performed on the hypersonic wind tunnel jet supplementary force measurement test data and the hypersonic wind tunnel conventional force measurement test data, and the influence of the jet interference after the jet medium parameters are adjusted is calculated; S40 and S50 are repeated until the influence of the jet interference meets the pre-set test requirements, and the jet medium parameters considering the influence of the jet interference are determined; S60. Establishing a jet state table for the attitude control jet engine of the slender body aircraft; According to the test results of S50, the jet state table of the attitude control jet engine of the slender body aircraft is established to guide the jet work of the attitude control jet engine of the slender body aircraft.

[0012] The test and evaluation device for the aerodynamic interference effect of the slender body attitude control jet of the present invention adopts an annular structure aerodynamic measurement balance. By arranging the jet pipeline inside the balance, the internal space of the slender body aircraft can be fully utilized, the structure of the test and evaluation device can be simplified, and the measurement accuracy and precision of the aerodynamic measurement balance within a larger load measurement range can be ensured; at the same time, a semiconductor strain gauge with high strain sensitivity is pasted on the sensitive element of the annular structure aerodynamic measurement balance, which improves the dynamic response characteristics of the aerodynamic measurement balance and can adapt to the time requirement (about 100ms) for the jet engine to establish a stable flow during the attitude control jet force measurement test.

[0013] The experimental evaluation method of the aerodynamic interference effect of the attitude control jet of the slender body shape of the present invention combines jet simulation and balance force measurement, and can truly simulate the flight state of the slender body aircraft in the hypersonic ground test. The experimental conclusions obtained have practical engineering value and provide technical support for the design and installation of the attitude control jet engine of the slender body aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a schematic structural diagram of the test and evaluation device for the aerodynamic interference effect of the attitude control jet of the slender body shape of the present invention; Figure 2a It is a structural schematic diagram (front view) of an aerodynamic force measurement balance in the test and evaluation device for the aerodynamic interference effect of the attitude control jet of a slender body shape of the present invention; Figure 2b It is a schematic structural diagram (top view) of an aerodynamic force measurement balance in the test and evaluation device for the aerodynamic interference effect of the attitude control jet of a slender body shape of the present invention; Figure 3 The present invention is a schematic diagram of the structure of a semiconductor strain gauge of an aerodynamic force measurement balance in the test and evaluation device for the aerodynamic interference effect of a slender body attitude control jet.

[0015] In the figure, 1. aircraft model; 2. nozzle; 3. sieve core tube; 4. aerodynamic measurement balance; 5. jet support rod; 6. jet air inlet; A1~A4 represent four semiconductor strain gauges for measuring the axial force A; N1~N4 represent four semiconductor strain gauges for measuring the normal force N; Z1~Z4 represent four semiconductor strain gauges for measuring the lateral force Z; Mx1~Mx4 represent four semiconductor strain gauges for measuring the rolling moment Mx; My1~My4 represent four semiconductor strain gauges for measuring the yaw moment My; Mz1~Mz4 represent four semiconductor strain gauges for measuring the pitch moment Mz; R0 is the zero compensation resistor of the semiconductor strain gauge; R1~R4 are four equal-resistance and mutually orthogonal varistors of the semiconductor strain gauge; RT0 is the temperature drift compensation resistor of the semiconductor strain gauge; RTF1~RTF2 are two sensitivity compensation resistors of the semiconductor strain gauge. DETAILED DESCRIPTION

[0016] The present invention is described in detail below with reference to the accompanying drawings and embodiments.

[0017] Example: Figure 1As shown, the test and evaluation device for the aerodynamic interference effect of the attitude control jet with a slender body shape of the present embodiment comprises a nozzle bracket, a sieve core tube 3 and an aerodynamic measurement balance 4 which are located in the inner cavity of the aircraft model 1 and are sequentially connected from front to back; Figure 2a , Figure 2b As shown, the aerodynamic measurement balance 4 adopts a ring structure, and a semiconductor strain gauge is attached to the sensitive element of the balance; the rear end of the aerodynamic measurement balance 4 is connected to a jet support rod 5, and a jet air inlet 6 is opened on the jet support rod 5; On the central axis of the aircraft model 1, a jet pipe is provided which sequentially passes through the nozzle bracket, the sieve core tube 3, the aerodynamic measurement balance 4 and the jet support rod 5, and the jet pipe is connected to the jet air inlet 6; A plurality of nozzles 2 are fixed on the nozzle bracket, and each nozzle 2 passes through the corresponding through hole on the aircraft model 1 and out of the aircraft model 1 . An annular gap is provided between the outlet of each nozzle 2 and the corresponding through hole, and the outlet of each nozzle 2 has a smooth transition with the surface of the aircraft model 1 .

[0018] Furthermore, a pressure monitoring hole is arranged on the sieve-like core tube 3 for monitoring the pressure of the jet chamber; and for adjusting the jet pressure of each nozzle 2 in the chamber.

[0019] Furthermore, the aerodynamic force measurement balance 4 is a ring-type six-component balance, the front section of which is provided with a parallelogram flexible assembly for measuring axial force, and the rear section is provided with a four-column beam measuring element for measuring normal force, lateral force, pitch moment, yaw moment and roll moment.

[0020] Furthermore, if Figure 3 As shown, four varistors with equal resistance are arranged on the semiconductor strain gauge, and a Wheatstone bridge is formed to reduce the temperature effect and take into account the sensitivity and frequency response requirements of the aerodynamic measurement balance 4.

[0021] The test and evaluation method of the aerodynamic interference effect of the attitude control jet of the slender body shape of the present embodiment comprises the following steps: S10. Conduct conventional force measurement tests in hypersonic wind tunnels; Prepare a routine test schedule, follow the routine force measurement test process of the hypersonic wind tunnel, change the sideslip angle, roll angle and angle of attack of the aircraft model 1 in sequence, and complete the routine force measurement test of the hypersonic wind tunnel; S20. Conduct hypersonic wind tunnel jet force measurement test; According to the flight state of the slender aircraft, the corresponding test state is selected in the conventional test plan table to carry out the jet force measurement test; during the jet force measurement test, the jet medium after pressure and temperature adjustment is introduced into the jet pipe through the jet air inlet 6, and then ejected through the nozzle 2 outlet to complete the hypersonic wind tunnel jet force measurement test; S30. Determine the impact amount of jet interference; The hypersonic wind tunnel jet force measurement test data and the conventional hypersonic wind tunnel force measurement test data were compared and analyzed to determine the influence of the jet interference. S40. Conduct supplementary force measurement test of hypersonic wind tunnel jet; Adjust the jet medium parameters and conduct supplementary force measurement tests on the hypersonic wind tunnel jet; S50. Determine the jet medium parameters taking into account the jet interference effect; Comparative analysis is performed on the hypersonic wind tunnel jet supplementary force measurement test data and the hypersonic wind tunnel conventional force measurement test data, and the influence of the jet interference after the jet medium parameters are adjusted is calculated; S40 and S50 are repeated until the influence of the jet interference meets the pre-set test requirements, and the jet medium parameters considering the influence of the jet interference are determined; S60. Establishing a jet state table for the attitude control jet engine of the slender body aircraft; According to the test results of S50, the jet state table of the attitude control jet engine of the slender body aircraft is established to guide the jet work of the attitude control jet engine of the slender body aircraft.

[0022] Although the embodiments of the present invention have been disclosed above, they are not limited to the applications listed in the description and the embodiments, and can be fully applied to various fields suitable for the present invention. For those familiar with the art, additional improvements and modifications can be easily realized without departing from the principles of the present invention. Therefore, without departing from the general concept defined by the claims and equivalent scope, the present invention is not limited to the specific details and the illustrations shown and described here.

Claims

1. An experimental evaluation device for the aerodynamic interference effect of a slender body attitude control jet, characterized in that: The test evaluation device comprises a nozzle support, a sieve core tube (3) and an aerodynamic measurement balance (4) which are located in the inner cavity of an aircraft model (1) and are connected in sequence from front to back; the aerodynamic measurement balance (4) adopts a ring structure, and a semiconductor strain gauge is attached to the sensitive element of the balance; the rear end of the aerodynamic measurement balance (4) is connected to a jet support rod (5), and a jet air inlet (6) is opened on the jet support rod (5); A jet pipe is provided on the central axis of the aircraft model (1) and passes through the nozzle bracket, the sieve core tube (3), the aerodynamic measurement balance (4) and the jet support rod (5) in sequence, and the jet pipe is connected to the jet air inlet (6); A plurality of nozzles (2) are fixed on the nozzle bracket, each nozzle (2) passes through a corresponding through hole on the aircraft model (1) and out of the aircraft model (1), an annular gap is provided between the outlet of each nozzle (2) and the corresponding through hole, and the outlet of each nozzle (2) and the surface of the aircraft model (1) have a smooth transition.

2. The test and evaluation device for the aerodynamic interference effect of the attitude control jet of the slender body according to claim 1 is characterized in that: The sieve-shaped core tube (3) is provided with a pressure monitoring hole for monitoring the pressure of the jet chamber; and for adjusting the jet pressure of each nozzle (2) in the chamber.

3. The test and evaluation device for the aerodynamic interference effect of the attitude control jet of the slender body according to claim 1 is characterized in that: The aerodynamic force measurement balance (4) is a ring-type six-component balance, the front section of which is provided with a parallelogram flexible assembly for measuring axial force, and the rear section of which is provided with a four-column beam measuring element for measuring normal force, lateral force, pitch moment, yaw moment and roll moment.

4. The test and evaluation device for the aerodynamic interference effect of the attitude control jet of the slender body according to claim 1 is characterized in that: The semiconductor strain gauge is provided with four piezoresistors of equal resistance and forms a Wheatstone bridge, which is used to reduce the temperature effect and take into account the sensitivity and frequency response requirements of the aerodynamic measurement balance (4).

5. A test and evaluation method for the aerodynamic interference effect of an attitude control jet having a slender body shape, which is used in a test and evaluation device for the aerodynamic interference effect of an attitude control jet having a slender body shape as claimed in any one of claims 1 to 4, characterized in that: The following steps are involved: S10. Conduct conventional force measurement tests in hypersonic wind tunnels; Prepare a routine test schedule, and follow the routine force measurement test process of the hypersonic wind tunnel to sequentially change the sideslip angle, roll angle, and angle of attack of the aircraft model (1) to complete the routine force measurement test of the hypersonic wind tunnel; S20. Conduct hypersonic wind tunnel jet force measurement test; According to the flight state of the slender aircraft, a corresponding test state is selected in the conventional test plan table to carry out a jet force measurement test; during the jet force measurement test, the jet medium after pressure and temperature adjustment is introduced into the jet pipe through the jet air inlet (6) and then ejected through the nozzle (2) outlet to complete the hypersonic wind tunnel jet force measurement test; S30. Determine the impact amount of jet interference; The hypersonic wind tunnel jet force measurement test data and the conventional hypersonic wind tunnel force measurement test data were compared and analyzed to determine the influence of the jet interference. S40. Conduct supplementary force measurement test of hypersonic wind tunnel jet; Adjust the jet medium parameters and conduct supplementary force measurement tests on the hypersonic wind tunnel jet; S50. Determine the jet medium parameters taking into account the jet interference effect; Comparative analysis is performed on the hypersonic wind tunnel jet supplementary force measurement test data and the hypersonic wind tunnel conventional force measurement test data, and the influence of the jet interference after the jet medium parameters are adjusted is calculated; S40 and S50 are repeated until the influence of the jet interference meets the pre-set test requirements, and the jet medium parameters considering the influence of the jet interference are determined; S60. Establishing a jet state table for the attitude control jet engine of the slender body aircraft; According to the test results of S50, the jet state table of the attitude control jet engine of the slender body aircraft is established to guide the jet work of the attitude control jet engine of the slender body aircraft.

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