CN110779616A - Flight test sonic boom signal measuring method - Google Patents
Flight test sonic boom signal measuring method Download PDFInfo
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- CN110779616A CN110779616A CN201911030655.2A CN201911030655A CN110779616A CN 110779616 A CN110779616 A CN 110779616A CN 201911030655 A CN201911030655 A CN 201911030655A CN 110779616 A CN110779616 A CN 110779616A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01H—MEASUREMENT OF MECHANICAL VIBRATIONS OR ULTRASONIC, SONIC OR INFRASONIC WAVES
- G01H11/00—Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves by detecting changes in electric or magnetic properties
- G01H11/06—Measuring mechanical vibrations or ultrasonic, sonic or infrasonic waves by detecting changes in electric or magnetic properties by electric means
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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Abstract
The invention discloses a flight test acoustic explosion signal measuring method, which comprises the following steps: the measuring device comprises capacitance type low-frequency microphones, a preamplifier, a data collector and a portable computer, wherein a plurality of capacitance type low-frequency microphones are adopted at each measuring point, the preamplifiers are respectively configured to form a microphone array, the microphone array is electrically connected with the data collector, the data collector is electrically connected with the portable computer, the data collection is started before an aircraft reaches the upper space of a measuring area, the data collection is stopped after the sonic boom signal is successfully measured, and the sonic boom signal obtained by measurement is analyzed and processed in the data collection time period. The invention can realize the accurate measurement of the ground sonic boom signal of the supersonic aircraft.
Description
Technical Field
The invention belongs to the technical field of an aerodynamic flight test, and particularly relates to a flight test acoustic explosion signal measuring method.
Background
The new generation of environment-friendly supersonic civil aircraft has become a hot research field of the world in the strong aviation countries, and the problem of sonic boom caused by the aircraft flying at supersonic speed has been a key technical problem which troubles the development of supersonic civil aircraft. The high-precision and high-reliability sound explosion prediction technology is the basis for developing the aerodynamic layout design of the low-sound-explosion supersonic civil aircraft. The research on the sonic boom problem mainly comprises three means, namely numerical simulation, wind tunnel test and flight test, the flight test capable of carrying out sonic boom characteristic research under real atmospheric conditions is a direct verification means of the sonic boom prediction technology, and the method has very important significance in the aspects of developing the supersonic civil aircraft aerodynamic theory, establishing the high-precision sonic boom prediction technology, exploring the sonic boom inhibition method and the like.
The measurement study of the problem of acoustic explosions in flight tests generally involves two aspects: firstly, before a sonic boom signal is transmitted to the ground, a detection airplane or a captive balloon is used as a platform to measure in a near field, a middle field or a far field of a supersonic aircraft; and secondly, after the sonic boom signal is propagated to the ground, measuring by using acoustic measuring equipment nearby the ground. The ground sonic boom signal is directly related to the visual perceptibility of people to sonic boom noise and the destructiveness of ground buildings, so the ground sonic boom signal measuring method of the supersonic aircraft is urgently needed to be invented.
Disclosure of Invention
Based on the defects, the invention provides the flight test sonic boom signal measuring method which can realize the accurate measurement of the ground sonic boom signal of the supersonic aircraft.
The technology adopted by the invention is as follows: a flight test sonic boom signal measuring method comprises the following steps: the measuring device comprises capacitance type low-frequency microphones, a preamplifier, a data collector and a portable computer, wherein a plurality of capacitance type low-frequency microphones are adopted at each measuring point, the preamplifiers are respectively configured to form a microphone array, the microphone array is electrically connected with the data collector, the data collector is electrically connected with the portable computer, the data collection is started before an aircraft reaches the upper space of a measuring area, the data collection is stopped after the sonic boom signal is successfully measured, and the sonic boom signal obtained by measurement is analyzed and processed in the data collection time period.
The specific calculation method for the measurement position of the ground sonic boom signal is as follows: according to the flight Mach number M, M is larger than 1, the Mach angle a is obtained through calculation, and the calculation formula is as follows:
according to the basic theory of geometric acoustics, the acoustic ray is perpendicular to the Mach cone, the horizontal distance x of the acoustic explosion signal generated by the supersonic aircraft at a certain position at a certain moment and transmitted to the ground is calculated according to the flight altitude h and the Mach angle a, and the calculation formula is as follows:
therefore, the ground sonic boom signal measuring position corresponding to the sonic boom signal generated by the supersonic aircraft at the position at the moment is obtained, namely the ground sonic boom signal measuring position is obtained by increasing the x distance along the flight direction on the basis of the ground coordinate of the supersonic aircraft at the moment.
The invention has the advantages and beneficial effects that: according to the flight parameters, the propagation direction of the supersonic aircraft sound explosion signal and the specific position of the supersonic aircraft sound explosion signal propagated to the ground at any moment can be calculated, and the precise measurement of the supersonic aircraft ground sound explosion signal is realized.
Drawings
FIG. 1 is a schematic diagram of calculation of a measurement position of a ground sonotrode signal of a supersonic aircraft;
FIG. 2 is a plan view of a supersonic aircraft ground sonotrode signal measurement system;
FIG. 3 is a component diagram of a supersonic aircraft ground sonotrode signal measurement sensor;
1. supersonic aircraft, 2, flight direction, 3, acoustic ray, 4, ground, 5, Mach cone, 6, measurement position, 7, microphone array, 8, data collector, 9, portable computer, 10, fan housing, 11, low frequency microphone, 12, adapter, 13 and preamplifier.
Detailed Description
The invention is described in further detail below with reference to the examples of the drawings.
Example 1
As shown in fig. 1-3, a method for measuring a sonic boom signal in a flight test comprises the following steps: firstly, calculating the measurement position of the ground sonic boom signal according to the flight parameters of the supersonic aircraft. According to the basic theory of geometric acoustics, an acoustic ray is perpendicular to a wave front, the tangential direction of any point on the acoustic ray represents the propagation direction of an acoustic signal, specifically to a supersonic aircraft, the aircraft flying at high altitude from a macroscopic scale can be regarded as a point sound source, when the aircraft flies at supersonic speed, the propagation direction of a sonic boom signal is perpendicular to a Mach cone, and the propagation direction of the sonic boom signal of the supersonic aircraft at any moment and the specific position of the sonic boom signal propagated to the ground are calculated according to the parameters of the flying Mach number, the flying height and the attitude angle, so that the measurement position of the ground sonic boom signal is obtained.
And then, selecting an optimal measurement system composition scheme according to the characteristics of the sonic boom signal and the test characteristics. In various types of sound pressure measuring sensors, the capacitive microphone has the advantages of high sensitivity, wide dynamic range, good frequency response characteristic and the like, and because the energy of the sound explosion signal is mainly concentrated in low frequency, the capacitive low-frequency microphone is selected, the preamplifier and the data collector are selected in a matching way, the low-frequency microphone and the preamplifier can be connected through an adapter, the preamplifier and the data collector are connected through a cable, the data collector and a portable computer are connected through a network cable, the data collector is powered by a storage battery, and the portable computer is used for controlling the collector and storing the sound explosion signal measuring data in real time.
And finally, reasonably arranging measuring equipment according to specific flight conditions and environmental conditions of a measuring area, and acquiring and storing ground sonic boom signal data of the supersonic aircraft. At each measuring point, four capacitance type low-frequency microphones are adopted and respectively provided with a preamplifier, the four capacitance type low-frequency microphones are connected with a four-channel data acquisition unit through four cables, and the data acquisition unit is connected with a portable computer through a cable. According to the battery endurance time of the measuring equipment, data acquisition is started before the aircraft arrives above the measuring area, data acquisition is stopped after the sonic boom signal is successfully measured, and the measured sonic boom signal is analyzed and processed in the data acquisition time period.
Example 2
A method for measuring a ground sonic boom signal in a flight test comprises the following steps of firstly, calculating the measurement position of the ground sonic boom signal according to flight parameters of a supersonic aircraft. The Mach angle a can be calculated according to the flight Mach number M (M is more than 1), and the calculation formula is as follows:
according to the basic theory of geometric acoustics, the acoustic ray is perpendicular to the Mach cone, the horizontal distance x of the acoustic explosion signal generated by the supersonic aircraft at a certain position at a certain moment and transmitted to the ground can be calculated according to the flight altitude h and the Mach angle a, and the calculation formula is as follows:
therefore, the ground sonic boom signal measuring position corresponding to the sonic boom signal generated by the supersonic aircraft at the position at the moment is obtained, namely the ground sonic boom signal measuring position is obtained by increasing the x distance along the flight direction on the basis of the ground coordinate of the supersonic aircraft at the moment.
And then, selecting an optimal measurement system composition scheme according to the characteristics of the sonic boom signal and the test characteristics. Because the energy of the sound explosion signal is mainly concentrated in low frequency, a capacitance type low-frequency microphone is selected as a ground sound explosion signal measuring sensor, the low-frequency microphone is connected with a preamplifier through an adapter, and the low-frequency microphone is wrapped by a fan cover so as to reduce the influence of wind noise. The microphone is connected with the data acquisition unit through a cable, and the data acquisition unit is connected with the portable computer through a network cable. The data collector adopts a built-in storage battery for power supply, and the portable computer is used for controlling the collector and storing the acoustic explosion signal measurement data in real time.
And finally, reasonably arranging measuring equipment according to specific flight conditions and environmental conditions of a measuring area, and acquiring and storing ground sonic boom signal data of the supersonic aircraft. And reasonably selecting the positions and the number of the measuring points according to the geographic position and the environmental condition of the measuring area. At each measuring point, four capacitance type low-frequency microphones are adopted and respectively provided with preamplifiers to form a microphone array, the microphone array is connected with a four-channel data acquisition device through four cables, the data acquisition device is connected with a portable computer through a cable, the four microphones can be arranged on a flat plate with enough area, and a support can be adopted to fix the four microphones at a certain height from the ground. According to the battery endurance time of the measuring equipment, data acquisition is started before the aircraft arrives above the measuring area, data acquisition is stopped after the sonic boom signal is successfully measured, and the measured sonic boom signal is analyzed and processed in the data acquisition time period.
Claims (2)
1. A flight test sonic boom signal measurement method is characterized by comprising the following steps: the measuring device comprises capacitance type low-frequency microphones, a preamplifier, a data collector and a portable computer, wherein a plurality of capacitance type low-frequency microphones are adopted at each measuring point, the preamplifiers are respectively configured to form a microphone array, the microphone array is electrically connected with the data collector, the data collector is electrically connected with the portable computer, the data collection is started before an aircraft reaches the upper space of a measuring area, the data collection is stopped after the sonic boom signal is successfully measured, and the sonic boom signal obtained by measurement is analyzed and processed in the data collection time period.
2. The method for measuring the sonic boom signal in the flight test according to claim 1, characterized in that: the specific calculation method for the measurement position of the ground sonic boom signal is as follows: according to the flight Mach number M, M is larger than 1, the Mach angle a is obtained through calculation, and the calculation formula is as follows:
according to the basic theory of geometric acoustics, the acoustic ray is perpendicular to the Mach cone, the horizontal distance x of the acoustic explosion signal generated by the supersonic aircraft at a certain position at a certain moment and transmitted to the ground is calculated according to the flight altitude h and the Mach angle a, and the calculation formula is as follows:
therefore, the ground sonic boom signal measuring position corresponding to the sonic boom signal generated by the supersonic aircraft at the position at the moment is obtained, namely the ground sonic boom signal measuring position is obtained by increasing the x distance along the flight direction on the basis of the ground coordinate of the supersonic aircraft at the moment.
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| CN114524110A (en) * | 2022-03-30 | 2022-05-24 | 西北工业大学 | Rapid design method of rotating mute cone for supersonic civil aircraft |
| CN114925539A (en) * | 2022-06-01 | 2022-08-19 | 中国科学院计算机网络信息中心 | Acoustic explosion wave inversion method, device, equipment and storage medium |
| CN115046628A (en) * | 2022-08-17 | 2022-09-13 | 中国民航大学 | Civil aviation noise monitoring system based on rotating paraboloid acoustic antenna directional reception |
| CN115541003A (en) * | 2022-10-12 | 2022-12-30 | 中国航空研究院 | Method for improving airplane ground sound explosion testing precision based on linear sensor array |
| CN117574730A (en) * | 2023-11-28 | 2024-02-20 | 中国航空研究院 | Numerical prediction method for supersonic civil aircraft maneuvering flight focusing acoustic explosion |
| CN117928723A (en) * | 2024-01-26 | 2024-04-26 | 杭州爱华仪器有限公司 | Sound level meter, noise measurement system and fan housing automatic identification correction method |
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- 2019-10-28 CN CN201911030655.2A patent/CN110779616A/en active Pending
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114524110A (en) * | 2022-03-30 | 2022-05-24 | 西北工业大学 | Rapid design method of rotating mute cone for supersonic civil aircraft |
| CN114524110B (en) * | 2022-03-30 | 2023-03-10 | 西北工业大学 | Rapid design method of rotation body mute cone for supersonic civil aircraft |
| CN114925539A (en) * | 2022-06-01 | 2022-08-19 | 中国科学院计算机网络信息中心 | Acoustic explosion wave inversion method, device, equipment and storage medium |
| CN114925539B (en) * | 2022-06-01 | 2022-12-30 | 中国科学院计算机网络信息中心 | Acoustic explosion wave inversion method, device, equipment and storage medium |
| CN115046628A (en) * | 2022-08-17 | 2022-09-13 | 中国民航大学 | Civil aviation noise monitoring system based on rotating paraboloid acoustic antenna directional reception |
| CN115046628B (en) * | 2022-08-17 | 2022-11-01 | 中国民航大学 | Civil aviation noise monitoring system based on rotating paraboloid acoustic antenna directional reception |
| CN115541003A (en) * | 2022-10-12 | 2022-12-30 | 中国航空研究院 | Method for improving airplane ground sound explosion testing precision based on linear sensor array |
| CN117574730A (en) * | 2023-11-28 | 2024-02-20 | 中国航空研究院 | Numerical prediction method for supersonic civil aircraft maneuvering flight focusing acoustic explosion |
| CN117574730B (en) * | 2023-11-28 | 2024-05-10 | 中国航空研究院 | Numerical prediction method for supersonic civil aircraft maneuvering flight focusing acoustic explosion |
| CN117928723A (en) * | 2024-01-26 | 2024-04-26 | 杭州爱华仪器有限公司 | Sound level meter, noise measurement system and fan housing automatic identification correction method |
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