CN-121994450-A - Test device and method for measuring force by reverse jet flow interference of aircraft main engine

CN121994450ACN 121994450 ACN121994450 ACN 121994450ACN-121994450-A

Abstract

The invention discloses a test device and a test method for measuring force by reverse jet flow interference of an aircraft main engine. The device comprises a model main body, a jet flow generator, a force measuring balance system, a gas supply system and a data acquisition system, wherein the model main body is used for installing the model main body on a supporting rod of a wind tunnel test section, the jet flow generator is detachably installed at one end of the model main body, the cold jet flow generator or the hot jet flow generator can be selected according to requirements to be connected with the model main body, the force measuring balance system comprises a first force measuring balance used for measuring thrust generated by a main engine and a second force measuring balance used for measuring pneumatic interference force borne by the model main body, the gas supply system is used for supplying gas to the jet flow generator, and the data acquisition system is used for synchronously acquiring output signals of the first force measuring balance and the second force measuring balance to realize independent measurement of the thrust and the pneumatic interference force of the main engine. The test device provided by the invention can be widely applied to aerodynamic force measurement under the condition of large difference of high and low loads, and provides high-precision test data support for the design of the aircraft control system under the condition of reverse jet interference of the main engine.

Inventors

ZHANG XIAOLIANG
SUN RUIBIN
WANG XINCHEN
LIU YAOFENG
CAO NING
LIU YUWEI

Assignees

中国航天空气动力技术研究院

Dates

Publication Date: 20260508
Application Date: 20251229

Claims (10)

1. A test device for the disturbance of the force measurement of a reverse jet of a main engine of an aircraft, comprising: A model main body (1) provided with an equipment accommodating cavity inside; the support rod (2) is connected with the model main body (1) and is used for installing the model main body (1) on a wind tunnel test section; The jet flow generator (3) is detachably arranged at one end in the model main body (1), the jet flow generator (3) comprises a cold jet flow generator and a hot jet flow generator, and the cold jet flow generator or the hot jet flow generator is selected to be connected with the model main body (1) according to the requirements of the simulated working conditions; The force measuring balance system comprises a first force measuring balance (4) and a second force measuring balance (5) which are arranged in the model main body (1), wherein one end of the first force measuring balance (4) is connected with the jet flow generator (3), and the other end of the first force measuring balance is connected with the supporting rod (2) and is used for measuring thrust generated by a main engine; a gas supply system for supplying gas to the jet generator (3); The data acquisition system is used for synchronously acquiring output signals of the first force measuring balance (4) and the second force measuring balance (5) and realizing independent measurement of thrust and pneumatic interference force of the main engine.
2. The test device according to claim 1, characterized in that the air supply system comprises an air supply pipeline (6), the air supply pipeline (6) penetrates through the supporting rod (2), the first force measuring balance (4) is communicated with the jet flow generator (3), and the air supply pipeline (6) is in threaded connection with the jet flow generator (3).
3. The test device according to claim 1, wherein the jet generator (3) is cylindrical and matched with the first force measuring balance (4) and is connected with the first force measuring balance (4) through pins, and a gap is reserved between the jet generator (3) and the model main body (1) when the jet generator (3) is installed with the first force measuring balance (4) so as to ensure that the jet generator (3) is not contacted with the model main body (1) when being opened.
4. The test device of claim 1, wherein the cold jet generator uses normal temperature and high pressure air as jet media to simulate different thrust conditions by adjusting the air supply pressure.
5. The test device of claim 1, wherein the thermal jet generator is a gas generator for simulating a real engine on condition.
6. Test device according to claim 1, characterized in that the first force-measuring balance (4) and the second force-measuring balance (5) are spatially decoupled from one another, load transfer and measurement crosstalk are avoided, and the accuracy in the respective measuring ranges is ensured.
7. The test device according to claim 1, wherein the front end of the jet generator (3) is provided with a jet nozzle (301) and a jet flow storage chamber (302) is arranged in the jet generator for stabilizing jet flow pressure, the front end surface of the jet generator (3) is provided with a pressure sensor (7) for measuring the pressure of the jet flow storage chamber (302), and the jet nozzle (301) is opposite to the incoming flow direction and forms reverse jet flow.
8. Test device according to claim 1, characterized in that the end of the strut (2) remote from the first force-measuring balance (4) protrudes outside the model body (1).
9. A method for testing the disturbance of the flow of a reverse jet of a main engine of an aircraft, characterized in that it is based on a test device according to any one of claims 1 to 8, comprising the following steps: s1, selecting a cold jet flow generator or a hot jet flow generator according to test requirements, and installing the cold jet flow generator or the hot jet flow generator into the front end of a model main body (1); s2, installing the model main body (1) on a wind tunnel test section through a support rod (2), and connecting an air supply pipeline (6) with a data acquisition cable; S3, calibrating the first force measuring balance (4) and the second force measuring balance (5), and calibrating the measurement accuracy of the first force measuring balance and the second force measuring balance; s4, starting the wind tunnel, adjusting the Mach number of the incoming flow to a target working condition, and starting the jet flow generator after the flow field is stable; s5, synchronously acquiring output signals of the first force measuring balance (4) and the second force measuring balance (5) by a data acquisition system, and acquiring thrust data of a main engine and pneumatic disturbance force data received by the model main body (1); s6, changing the jet flow pressure ratio and the attack angle of the model main body (1), and carrying out a multi-working condition combination test; S7, analyzing test data, and evaluating the influence of reverse jet flow on the overall aerodynamic performance of the aircraft.
10. The test method according to claim 9, wherein cold spray and hot spray conditions are compared under the same aerodynamic profile and inflow conditions, respectively, to study the effect of the hot spray effect on aerodynamic disturbance characteristics.

Description

Test device and method for measuring force by reverse jet flow interference of aircraft main engine Technical Field The invention relates to the technical field of aerodynamic ground simulation tests, in particular to a test device and a test method for measuring force by reverse jet flow interference of an aircraft main engine, which are suitable for accurately measuring aerodynamic force/moment of a recoverable rocket, a recoverable cabin and the like, which face the problem of aerodynamic interference of the main jet flow. Background With the rapid development of recycling technology of reusable carrier rockets and return cabins, in the recycling process, a main engine is reversely ignited at low altitude to generate reverse thrust so as to realize deceleration and accurate landing. At this time, the reverse jet flow of the high-thrust main engine interacts with the high-speed incoming flow to form a remarkable pneumatic interference effect, and the resistance, the lifting force and the stability of the aircraft are directly influenced. The accurate acquisition of aerodynamic data under interference conditions is critical to the safe flight of an aircraft. At present, the research on the reverse jet interference of a main engine mainly depends on wind tunnel tests and numerical simulation, and in the existing wind tunnel test technology, a single force measuring balance support model is generally adopted and total aerodynamic force is measured. However, under the reverse jet opening working condition of the main engine, the thrust of the main engine is far greater than the pneumatic interference force (the two are different by nearly an order of magnitude), the single force measuring balance is difficult to ensure the measurement accuracy of high load thrust and low load interference force in the same measuring range, the reverse thrust generated by the jet and the interference force air intake generated by the jet-incoming flow interaction are difficult to be decoupled accurately, the deep understanding of the interference mechanism is limited, and the cold/hot jet simulation generally needs two sets of systems, so that the switching cost is high and time is consumed, and the exchange under the same test model strip is difficult. Therefore, the main engine reverse jet flow interference wind tunnel test system which can simultaneously meet the requirements of high fidelity, high efficiency, high precision measurement and strong adaptability is developed, and has important theoretical and engineering significance for promoting the progress of the pneumatic design of the recyclable rocket. Disclosure of Invention The invention aims to provide a test device and a test method for measuring force by reverse jet flow interference of an aircraft main engine, which are used for solving the problem of insufficient measurement precision caused by large magnitude difference between thrust and pneumatic interference force of the aircraft main engine in the prior art and realizing replaceable simulation of cold jet and hot jet working conditions. The invention provides a test device for measuring force by reverse jet flow interference of a main engine of an aircraft, which comprises the following components: the main body of the model is provided with a main body, an equipment accommodating cavity is formed in the inner part; The support rod is connected with the model main body and used for installing the model main body on the wind tunnel test section; The jet flow generator is detachably arranged at one end in the model main body, comprises a cold jet flow generator and a hot jet flow generator, and is connected with the model main body according to the requirements of the simulated working conditions; The force measuring balance system comprises a first force measuring balance and a second force measuring balance, wherein the first force measuring balance and the second force measuring balance are arranged in the model main body, one end of the first force measuring balance is connected with the jet flow generator, and the other end of the first force measuring balance is connected with the supporting rod and is used for measuring thrust generated by the main engine; a gas supply system for supplying gas to the jet generator; and the data acquisition system is used for synchronously acquiring output signals of the first force measuring balance and the second force measuring balance, and realizing independent measurement of thrust and pneumatic interference force of the main engine. Further, the air supply system comprises an air supply pipeline, the air supply pipeline penetrates through the supporting rod and the first force measuring balance to be communicated with the jet flow generator, and the air supply pipeline is in threaded connection with the jet flow generator. Furthermore, the jet flow generator is matched with the first force measuring balance through a cylindrical surface and is connected with the f