A method and system for designing parameters of variable-range telemetry antenna for aircraft engines

Abstract

The present invention relates to the field of aircraft engine technology, and discloses a method and system for designing parameters of aircraft engine variable-range telemetry antennas. According to the rotor-static space structural characteristics and the design requirements of the number of measurement points of the rotor, a coupling model of the aircraft engine variable-range telemetry antenna based on a transmitting antenna simulation model and a receiving antenna simulation model is established. The transmission coefficient variation curve of the variable-range telemetry antenna based on the transmitting antenna simulation model and the receiving antenna simulation model is solved by mode driving, and the performance analysis of the telemetry antenna under high-speed rotation, variable-range working conditions and different resonant frequencies is realized. The present invention uses the transmission coefficient variation curve and the preset transmission coefficient threshold to quickly determine the operating frequency band and rotor-static space working range of the variable-range telemetry antenna, ensuring that the variable-range telemetry antenna meets the stability and reliability of test data transmission under high-speed rotation and variable-range working conditions of the aircraft engine.

Description

Technical Field

[0001] The invention relates to the technical field of aeroengines, and discloses a method and a system for designing parameters of a variable-range telemetry antenna for an aeroengine. Background Art

[0002] In the aviation industry, scientific research test flights and test runs are essential for the development and mass production of aircraft and engines. Compared with the onboard equipment on the aircraft, the aircraft engine is always in a high-speed rotation state, and it is easy to fail in the continuous operation state, which will not only damage the equipment but also affect the production efficiency of the aviation industry, bring economic losses to the aviation industry, and even cause serious consequences such as casualties. Therefore, in order to improve the safety and reliability of rotating machinery, it is of great significance to study the transmission of dynamic parameters of rotating parts.

[0003] Telemetry antenna is a converter that converts electrical signals into free space electromagnetic wave signals, and is an important component of the telemetry device for high-speed rotating parts of aircraft engines. The parameter test of high-speed rotating parts of aircraft engines has the characteristics of high speed, constantly changing rotor-static distance, vibration, etc. The empirical design often requires multiple rounds of iterative test verification and improvement, which has the problems of long cycle, high development cost, and difficulty in evaluating antenna transmission performance, which greatly prolongs the test cycle of the engine. Summary of the invention

[0004] The purpose of the present invention is to provide a method and system for designing parameters of a variable-range telemetry antenna for an aircraft engine, which can ensure that the variable-range telemetry antenna meets the requirements of test data transmission stability and reliability under conditions of high-speed rotation and variable range of the aircraft engine.

[0005] In order to achieve the above technical effects, the technical solution adopted by the present invention is:

[0006] A method for designing parameters of an aircraft engine variable-range telemetry antenna, wherein the variable-range telemetry antenna comprises a transmitting antenna and a receiving antenna, wherein the transmitting antenna comprises a plurality of arc-shaped microstrip antennas arranged on a first PCB substrate, wherein the plurality of arc-shaped microstrip antennas are circumferentially distributed at the same radial height position of an engine rotor; wherein the receiving antenna comprises a second PCB substrate and a non-closed circular loop antenna structure fixed on the second PCB substrate, wherein the non-closed circular loop antenna structure is coaxially arranged opposite to the arc-shaped microstrip antenna; and wherein the design method comprises:

[0007] Determining the number of microstrip antennas in the transmitting antenna according to the number of measuring points of the aircraft engine rotor;

[0008] According to the width design value of the transmitting antenna, the design specification parameters of the first PCB substrate of the transmitting antenna, and the target resonant frequency of the variable-range telemetry antenna, a rectangular microstrip antenna length calculation method is used to analyze and obtain the length of the arc microstrip antenna, and the curvature of each microstrip antenna is analyzed according to the number of microstrip antennas;

[0009] Taking the width design value of the transmitting antenna as the width of the receiving antenna, a receiving antenna simulation model based on the second PCB substrate and a non-closed circular ring structure is constructed;

[0010] According to the number of microstrip antennas, the width design value of the transmitting antenna, and the curvature of each microstrip antenna, a transmitting antenna simulation model based on the first PCB substrate and the microstrip antenna is constructed;

[0011] Taking an air box of no less than 1 / 4 wavelength as a radiation boundary condition, under different spacing values ​​and different resonant frequency combinations between the transmitting antenna simulation model and the receiving antenna simulation model, the transmission coefficient variation curve of the variable-range telemetry antenna based on the transmitting antenna simulation model and the receiving antenna simulation model is solved by mode driving;

[0012] In the transmission coefficient variation curve, a resonant frequency range not less than a preset transmission coefficient threshold and a corresponding spacing value range are determined as the operating frequency band and the switching spacing working range of the variable-range telemetry antenna, respectively.

[0013] Furthermore, the curvature of each microstrip antenna ,in The length of the arc microstrip antenna is obtained by using the rectangular microstrip antenna length calculation method. , is the number of microstrip antennas in the transmitting antenna, For data value The ceiling function of .

[0014] Furthermore, the method for constructing a receiving antenna simulation model based on the second PCB substrate and the non-closed circular ring structure includes:

[0015] Take any point O in space as the origin and establish a Cartesian coordinate system O-XYZ;

[0016] Construct a non-closed circular line in the XOY plane with the origin O as the center ,in is the angle range of the non-closed circular line, The value range is , is the annular angle of the non-closed circular ring structure, is the coordinate value of the non-closed circular line on the X-axis, is the coordinate value of the non-closed circular line on the Y axis, is the coordinate value of the non-closed circular line on the Z axis;

[0017] In the XOY plane, the non-closed loop line is offset inwards and outwards respectively. , and connect the corresponding end points to form an arc-shaped belt; is the width of the receiving antenna;

[0018] The arc-shaped belt is offset along the positive direction of the Z axis by a certain thickness , forming a non-closed circular loop antenna structure with thickness;

[0019] The second PCB substrate is constructed in a plane along the negative direction of the Z axis and parallel to XOY; and one end of the non-closed circular loop antenna structure is grounded through a radio frequency resistor.

[0020] Furthermore, the method for constructing a simulation model of a transmitting antenna based on a first PCB substrate and a microstrip antenna includes:

[0021] Along the positive direction of the Z axis and at a distance from the XOY plane The first arc line is constructed in the first offset plane ,in is the angle range of the first arc line, The value range is , is the arc of the microstrip antenna, is the coordinate value of the first arc line on the X-axis, is the coordinate value of the first arc line on the Y axis, is the coordinate value of the first arc line on the Z axis, It is the distance between the rotor and the static of the aircraft engine;

[0022] In the first offset plane, the first arc line is offset inward and outward respectively. , and connect the corresponding endpoints to form a ring structure; Design value for the width of the transmitting antenna;

[0023] The ring belt structure is offset along the positive direction of the Z axis by a certain thickness , forming a ring-belt structure with a thickness; then according to the number of microstrip antennas in the transmitting antenna determined , the annular array is formed A circularly distributed arc-shaped microstrip antenna;

[0024] Along the positive direction of the Z axis and at a distance from the XOY plane The first PCB substrate is constructed in the second bias plane, and the arc-shaped microstrip antenna is fed through the coaxial line.

[0025] In order to achieve the above technical effects, the present invention also provides an aircraft engine variable-range telemetry antenna parameter design system for implementing the above design method; comprising:

[0026] A data acquisition module, used to determine the number of microstrip antennas in the transmitting antenna according to the number of measuring points of the aircraft engine rotor;

[0027] The first analysis module is used to analyze and obtain the length of the arc microstrip antenna using a rectangular microstrip antenna length calculation method according to the width design value of the transmitting antenna, the design specification parameters of the first PCB substrate of the transmitting antenna, and the target resonant frequency of the variable-range telemetry antenna, and to analyze and obtain the curvature of each microstrip antenna according to the number of microstrip antennas;

[0028] A simulation model construction module is used to construct a receiving antenna simulation model based on the second PCB substrate and a non-closed circular ring structure by taking the width design value of the transmitting antenna as the width of the receiving antenna; and to construct a transmitting antenna simulation model based on the first PCB substrate and the microstrip antenna according to the number of microstrip antennas, the width design value of the transmitting antenna and the curvature of each microstrip antenna;

[0029] A simulation analysis module is used to solve the transmission coefficient change curve of the variable-range telemetry antenna based on the transmitting antenna simulation model and the receiving antenna simulation model through mode driving under different spacing values ​​and different resonant frequency combinations between the transmitting antenna simulation model and the receiving antenna simulation model, using an air box of not less than 1 / 4 wavelength as a radiation boundary condition;

[0030] The parameter determination module is used to determine the resonant frequency range and the corresponding spacing value range that are not less than the preset transmission coefficient threshold in the transmission coefficient change curve, which are used as the working frequency band and the switching spacing working range of the variable-range telemetry antenna respectively.

[0031] Furthermore, in the first analysis module, Analyze the curvature of each microstrip antenna ,in The length of the arc microstrip antenna is obtained by using the rectangular microstrip antenna length calculation method. , is the number of microstrip antennas in the transmitting antenna, For data value The ceiling function of .

[0032] Furthermore, in the simulation model construction module, a method for constructing a receiving antenna simulation model based on a second PCB substrate and a non-closed circular ring structure includes:

[0033] Take any point O in space as the origin and establish a Cartesian coordinate system O-XYZ;

[0034] Construct a non-closed circular line in the XOY plane with the origin O as the center ,in is the angle range of the non-closed circular line, The value range is , is the annular angle of the non-closed circular ring structure, is the coordinate value of the non-closed circular line on the X-axis, is the coordinate value of the non-closed circular line on the Y axis, is the coordinate value of the non-closed circular line on the Z axis;

[0035] In the XOY plane, the non-closed loop line is offset inwards and outwards respectively. , and connect the corresponding end points to form an arc-shaped belt; is the width of the receiving antenna;

[0036] The arc-shaped belt is offset along the positive direction of the Z axis by a certain thickness , forming a non-closed circular loop antenna structure with thickness;

[0037] The second PCB substrate is constructed in a plane along the negative direction of the Z axis and parallel to XOY; and one end of the non-closed circular loop antenna structure is grounded through a radio frequency resistor.

[0038] Furthermore, in the simulation model construction module, a method for constructing a simulation model of a transmitting antenna based on a first PCB substrate and a microstrip antenna includes:

[0039] Along the positive direction of the Z axis and at a distance from the XOY plane The first arc line is constructed in the first offset plane ,in is the angle range of the first arc line, The value range is , is the arc of the microstrip antenna, is the coordinate value of the first arc line on the X-axis, is the coordinate value of the first arc line on the Y axis, is the coordinate value of the first arc line on the Z axis, It is the distance between the rotor and the static of the aircraft engine;

[0040] In the first offset plane, the first arc line is offset inward and outward respectively. , and connect the corresponding endpoints to form a ring structure; Design value for the width of the transmitting antenna;

[0041] The ring belt structure is offset along the positive direction of the Z axis by a certain thickness , forming a ring-belt structure with a thickness; then according to the number of microstrip antennas in the transmitting antenna determined , the annular array is formed A circularly distributed arc-shaped microstrip antenna;

[0042] Along the positive direction of the Z axis and at a distance from the XOY plane The first PCB substrate is constructed in the second bias plane, and the arc-shaped microstrip antenna is fed through the coaxial line.

[0043] Compared with the prior art, the present invention has the following beneficial effects: according to the structural characteristics of the rotor-stationary compartment and the design requirements of the number of measuring points of the rotor, the present invention establishes an aircraft engine variable-range telemetry antenna coupling model based on a transmitting antenna simulation model and a receiving antenna simulation model, and solves the variable-range telemetry antenna transmission coefficient variation curve S based on the transmitting antenna simulation model and the receiving antenna simulation model through mode driving. 21 , realizing the performance analysis of telemetry antenna under high-speed rotation, variable pitch working conditions and different resonant frequencies. 21 As well as the preset transmission coefficient threshold, the operating frequency band and rotation-to-static distance working range of the variable-range telemetry antenna can be quickly determined, ensuring that the variable-range telemetry antenna meets the requirements of test data transmission stability and reliability under high-speed rotation and variable-range conditions of aircraft engines. BRIEF DESCRIPTION OF THE DRAWINGS

[0044] Figure 1 It is a flow chart of the method for designing parameters of the variable-range telemetry antenna of an aircraft engine in Embodiment 1 or 2;

[0045] Figure 2 This is a structural block diagram of the aircraft engine variable-range telemetry antenna parameter design system in Example 1;

[0046] Figure 3 A schematic diagram of the position relationship between the transmitting antenna and the receiving antenna in Embodiment 1 or 2;

[0047] Figure 4 It is a schematic diagram of the transmitting antenna structure in Embodiment 1 or 2;

[0048] Figure 5 It is a curve diagram of the transmission coefficient change of the variable-range telemetry antenna in Example 2;

[0049] Among them, 1. a first PCB substrate; 2. an arc microstrip antenna; 3. a second PCB substrate; 4. a non-closed circular loop antenna structure; 5. a data acquisition module; 6. a first analysis module; 7. a simulation model building module; 8. a simulation analysis module; 9. a parameter determination module. DETAILED DESCRIPTION

[0050] The present invention is further described in detail below in conjunction with the embodiments and drawings. However, it should not be understood that the scope of the above subject matter of the present invention is limited to the following embodiments, and all technologies realized based on the content of the present invention belong to the scope of the present invention.

[0051] Example 1

[0052] See also Figure 1-Figure 4 A method for designing parameters of an aircraft engine variable-range telemetry antenna, wherein the variable-range telemetry antenna comprises a transmitting antenna and a receiving antenna, wherein the transmitting antenna comprises a plurality of arc-shaped microstrip antennas 2 arranged on a first PCB substrate 1, wherein the plurality of arc-shaped microstrip antennas 2 are circumferentially distributed at the same radial height position of an engine rotor; wherein the receiving antenna comprises a second PCB substrate 3 and a non-closed circular loop antenna structure 4 fixed on the second PCB substrate 3, wherein the non-closed circular loop antenna structure 4 is coaxially arranged opposite to the arc-shaped microstrip antenna 2; wherein the design method comprises:

[0053] Determining the number of microstrip antennas in the transmitting antenna according to the number of measuring points of the aircraft engine rotor;

[0054] According to the design value of the width of the transmitting antenna, the design specification parameters of the first PCB substrate 1 of the transmitting antenna and the target resonant frequency of the variable-range telemetry antenna, the length of the arc-shaped microstrip antenna 2 is obtained by using the rectangular microstrip antenna length calculation method, and the curvature of each microstrip antenna is obtained by analyzing the number of microstrip antennas;

[0055] Taking the design value of the width of the transmitting antenna as the width of the receiving antenna, a simulation model of the receiving antenna based on the second PCB substrate 3 and the non-closed circular ring structure is constructed;

[0056] According to the number of microstrip antennas, the design value of the width of the transmitting antenna, and the curvature of each microstrip antenna, a transmitting antenna simulation model based on the first PCB substrate 1 and the microstrip antenna is constructed;

[0057] Taking an air box of no less than 1 / 4 wavelength as a radiation boundary condition, under different spacing values ​​and different resonant frequency combinations between the transmitting antenna simulation model and the receiving antenna simulation model, the transmission coefficient variation curve of the variable-range telemetry antenna based on the transmitting antenna simulation model and the receiving antenna simulation model is solved by mode driving;

[0058] In the transmission coefficient variation curve, a resonant frequency range not less than a preset transmission coefficient threshold and a corresponding spacing value range are determined as the operating frequency band and the switching spacing working range of the variable-range telemetry antenna, respectively.

[0059] In this embodiment, according to the structural characteristics of the rotor-stationary compartment and the design requirements of the number of measuring points of the rotor, an aircraft engine variable-range telemetry antenna coupling model based on a transmitting antenna simulation model and a receiving antenna simulation model is established, and a variable-range telemetry antenna transmission coefficient variation curve S based on the transmitting antenna simulation model and the receiving antenna simulation model is solved by mode driving. 21 , realizing the performance analysis of telemetry antenna under high-speed rotation, variable pitch working conditions and different resonant frequencies. 21 As well as the preset transmission coefficient threshold, the operating frequency band and rotation-to-static distance working range of the variable-range telemetry antenna can be quickly determined, ensuring that the variable-range telemetry antenna meets the requirements of test data transmission stability and reliability under high-speed rotation and variable-range conditions of aircraft engines.

[0060] Based on the same inventive concept, this embodiment also provides an aircraft engine variable range telemetry antenna parameter design system, including:

[0061] The data acquisition module 5 is used to determine the number of microstrip antennas in the transmitting antenna according to the number of measuring points of the aircraft engine rotor;

[0062] The first analysis module 6 is used to analyze and obtain the length of the arc microstrip antenna 2 using a rectangular microstrip antenna length calculation method according to the width design value of the transmitting antenna, the design specification parameters of the first PCB substrate 1 of the transmitting antenna, and the target resonant frequency of the variable-range telemetry antenna, and to analyze and obtain the curvature of each microstrip antenna according to the number of microstrip antennas;

[0063] The simulation model construction module 7 is used to construct a simulation model of the receiving antenna based on the second PCB substrate 3 and the non-closed circular ring structure by taking the width design value of the transmitting antenna as the width of the receiving antenna; and to construct a simulation model of the transmitting antenna based on the first PCB substrate 1 and the microstrip antenna according to the number of microstrip antennas, the width design value of the transmitting antenna and the curvature of each microstrip antenna;

[0064] The simulation analysis module 8 is used to solve the transmission coefficient change curve of the variable-range telemetry antenna based on the transmitting antenna simulation model and the receiving antenna simulation model through mode driving under different spacing values ​​and different resonant frequency combinations between the transmitting antenna simulation model and the receiving antenna simulation model with an air box of not less than 1 / 4 wavelength as a radiation boundary condition;

[0065] The parameter determination module 9 is used to determine the resonant frequency range and the corresponding spacing value range that are not less than the preset transmission coefficient threshold in the transmission coefficient change curve, which are used as the working frequency band and the switching spacing working range of the variable-range telemetry antenna respectively.

[0066] Example 2

[0067] See also Figure 1 , Figure 3 and Figure 4 A method for designing parameters of an aircraft engine variable-range telemetry antenna, wherein the variable-range telemetry antenna comprises a transmitting antenna and a receiving antenna, wherein the transmitting antenna comprises a plurality of arc-shaped microstrip antennas 2 arranged on a first PCB substrate 1, wherein the plurality of arc-shaped microstrip antennas 2 are circumferentially distributed at the same radial height position of an engine rotor; wherein the receiving antenna comprises a second PCB substrate 3 and a non-closed circular loop antenna structure 4 fixed on the second PCB substrate 3, wherein the non-closed circular loop antenna structure 4 is coaxially arranged opposite to the arc-shaped microstrip antenna 2; wherein the design method comprises the following steps:

[0068] Step 1: determining the number of microstrip antennas in the transmitting antenna according to the number of measuring points of the aircraft engine rotor;

[0069] Step 2: According to the width design value of the transmitting antenna, the design specification parameters of the first PCB substrate 1 of the transmitting antenna, and the target resonant frequency of the variable-range telemetry antenna, the rectangular microstrip antenna length calculation method is used to analyze and obtain the length of the arc microstrip antenna 2, and the curvature of each microstrip antenna is analyzed according to the number of microstrip antennas;

[0070] In this embodiment, the curvature of each microstrip antenna ,in The length of the arc microstrip antenna 2 is obtained by using the rectangular microstrip antenna length calculation method. , is the number of microstrip antennas in the transmitting antenna, For data value The ceiling function of .

[0071] It should be noted that the parameters involved in the process of using the rectangular microstrip antenna length calculation method to analyze and obtain the length of the arc microstrip antenna 2 include the width design value of the transmitting antenna , target resonant frequency of variable-range telemetry antenna , the first PCB substrate 1 is designed to have a thickness and the dielectric constant of the first PCB substrate 1 This calculation method is a technical solution well known to those skilled in the art and will not be described in detail here.

[0072] Step 3: Using the design value of the width of the transmitting antenna as the width of the receiving antenna, a receiving antenna simulation model based on the second PCB substrate 3 and a non-closed circular ring structure is constructed;

[0073] In this embodiment, the steps of constructing a receiving antenna simulation model based on the second PCB substrate 3 and a non-closed circular ring structure are as follows:

[0074] 3.1. Take any point O in space as the origin and establish a Cartesian coordinate system O-XYZ;

[0075] 3.2. Construct a non-closed circular line in the XOY plane with the origin O as the center ,in is the angle range of the non-closed circular line, The value range is , is the annular angle of the non-closed circular ring structure. The value range is , is the coordinate value of the non-closed circular line on the X-axis, is the coordinate value of the non-closed circular line on the Y axis, is the coordinate value of the non-closed circular line on the Z axis;

[0076] 3.3. In the XOY plane, offset the non-closed loop line inwards and outwards respectively , and connect the corresponding end points to form an arc-shaped belt;

[0077] 3.4. Offset the arc belt along the positive direction of the Z axis by a certain thickness , forming a non-closed circular loop antenna structure 4 with thickness;

[0078] 3.5. Construct the diameter in the plane along the negative direction of the Z axis and parallel to XOY. , the dielectric constant is ,high A cylindrical PCB medium is used to form the second PCB substrate 3; one end of the non-closed circular ring antenna structure 4 is grounded through a radio frequency resistor.

[0079] Step 4: According to the number of microstrip antennas , Design value of transmitting antenna width And the curvature of each microstrip antenna , constructing a transmitting antenna simulation model based on the first PCB substrate 1 and the microstrip antenna;

[0080] In this embodiment, the method steps for constructing a transmitting antenna simulation model based on the first PCB substrate 1 and the microstrip antenna are as follows:

[0081] 4.1. Along the positive direction of the Z axis and away from the XOY plane The first arc line is constructed in the first offset plane ,in is the angle range of the first arc line, The value range is , is the coordinate value of the first arc line on the X-axis, is the coordinate value of the first arc line on the Y axis, is the coordinate value of the first arc line on the Z axis, It is the distance between the rotor and the static of the aircraft engine;

[0082] 4.2. In the first offset plane, the first arc line is offset inward and outward respectively. , and connect the corresponding endpoints to form a ring structure;

[0083] 4.2. Offset the ring belt structure along the positive direction of the Z axis by a certain thickness , forming a ring-belt structure with a thickness; then according to the number of microstrip antennas in the transmitting antenna determined , the annular array is formed A circularly distributed arc-shaped microstrip antenna 2; in this embodiment, The target resonant frequency corresponding to the arc-shaped microstrip antenna 2 The number should be less than or equal to the number of non-overlapping channels in the operating frequency band of the transmitting antenna;

[0084] 4.3. Along the positive direction of the Z axis and away from the XOY plane In the second offset plane, the diameter is constructed , the dielectric constant is ,high A cylindrical PCB medium is used to form the first PCB substrate 1; and the arc-shaped microstrip antenna 2 is fed through a coaxial line.

[0085] In this embodiment, the first PCB substrate 1 of the transmitting antenna , The value range is usually [2.5mm, 3mm], Take 4.4, The value range is [1.2mm, 3mm], and the RF resistance is 50Ω. The value range is 35um or 70um, preferably 35um;

[0086] The second PCB substrate 3 of the receiving antenna ， , Take 4.4, The value range is [1.2mm, 3mm], The value range is 35um or 70um, preferably 35um.

[0087] Step 5: Use an air box no smaller than 1 / 4 wavelength as the radiation boundary condition, and adjust the distance between the transmitting antenna simulation model and the receiving antenna simulation model (i.e. adjust the distance between the transmitting antenna and the receiving antenna). value) and different resonant frequency combinations, the transmission coefficient variation curve S of the variable-range telemetry antenna based on the transmitting antenna simulation model and the receiving antenna simulation model is solved by mode driving. 21 (like Figure 5 shown);

[0088] Step 6: In the transmission coefficient variation curve S 21 Determine the resonant frequency range and the corresponding spacing value range that are not less than the preset transmission coefficient threshold value, which are used as the working frequency band and the switching spacing working range of the variable-range telemetry antenna respectively;

[0089] In this embodiment, select S in step 5 21 The spacing value range of amplitude ≮-40dB is used as the normal transmission distance range between the transmitting antenna and the receiving antenna. 21 The resonant frequency range with an amplitude ≮-40dB is the frequency range in which the transmitting antenna and the receiving antenna can work normally.

[0090] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A method for designing parameters of a variable-range telemetry antenna for an aircraft engine, wherein the variable-range telemetry antenna comprises a transmitting antenna and a receiving antenna, wherein the transmitting antenna comprises a plurality of arc-shaped microstrip antennas arranged on a first PCB substrate, wherein the plurality of arc-shaped microstrip antennas are circumferentially distributed at the same radial height position of an engine rotor; wherein the receiving antenna comprises a second PCB substrate and a non-closed circular loop antenna structure fixed on the second PCB substrate, wherein the non-closed circular loop antenna structure is coaxially arranged opposite to the arc-shaped microstrip antenna; wherein: The design method comprises: Determining the number of microstrip antennas in the transmitting antenna according to the number of measuring points of the aircraft engine rotor; According to the width design value of the transmitting antenna, the design specification parameters of the first PCB substrate of the transmitting antenna and the target resonant frequency of the variable-range telemetry antenna, the length of the arc microstrip antenna is obtained by using the rectangular microstrip antenna length calculation method, and the arc of each microstrip antenna is obtained by analyzing the number of microstrip antennas. ,in The length of the arc microstrip antenna is obtained by using the rectangular microstrip antenna length calculation method. , is the number of microstrip antennas in the transmitting antenna, For data value The ceiling function of ; Taking the width design value of the transmitting antenna as the width of the receiving antenna, a receiving antenna simulation model based on the second PCB substrate and a non-closed circular ring structure is constructed; According to the number of microstrip antennas, the width design value of the transmitting antenna, and the curvature of each microstrip antenna, a transmitting antenna simulation model based on the first PCB substrate and the microstrip antenna is constructed; Taking an air box of no less than 1 / 4 wavelength as a radiation boundary condition, under different spacing values ​​and different resonant frequency combinations between the transmitting antenna simulation model and the receiving antenna simulation model, the transmission coefficient variation curve of the variable-range telemetry antenna based on the transmitting antenna simulation model and the receiving antenna simulation model is solved by mode driving; In the transmission coefficient variation curve, a resonant frequency range not less than a preset transmission coefficient threshold and a corresponding spacing value range are determined as the operating frequency band and the switching spacing working range of the variable-range telemetry antenna, respectively.

2. The design method according to claim 1, characterized in that: The method for constructing a receiving antenna simulation model based on a second PCB substrate and a non-closed circular ring structure includes: Take any point O in space as the origin and establish a Cartesian coordinate system O-XYZ; Construct a non-closed circular line in the XOY plane with the origin O as the center ,in is the angle range of the non-closed circular line, The value range is , is the annular angle of the non-closed circular ring structure, is the coordinate value of the non-closed circular line on the X-axis, is the coordinate value of the non-closed circular line on the Y axis, is the coordinate value of the non-closed circular line on the Z axis; In the XOY plane, the non-closed loop line is offset inwards and outwards respectively. , and connect the corresponding end points to form an arc-shaped belt; is the width of the receiving antenna; The arc-shaped belt is offset along the positive direction of the Z axis by a certain thickness , forming a non-closed circular loop antenna structure with thickness; The second PCB substrate is constructed in a plane along the negative direction of the Z axis and parallel to XOY; and one end of the non-closed circular loop antenna structure is grounded through a radio frequency resistor.

3. The design method according to claim 2, characterized in that: The method for constructing a simulation model of a transmitting antenna based on a first PCB substrate and a microstrip antenna includes: Along the positive direction of the Z axis and at a distance from the XOY plane The first arc line is constructed in the first offset plane ,in is the angle range of the first arc line, The value range is , is the arc of the microstrip antenna, is the coordinate value of the first arc line on the X-axis, is the coordinate value of the first arc line on the Y axis, is the coordinate value of the first arc line on the Z axis, It is the distance between the rotor and the static of the aircraft engine; In the first offset plane, the first arc line is offset inward and outward respectively. , and connect the corresponding endpoints to form a ring structure; Design value for the width of the transmitting antenna; The ring belt structure is offset along the positive direction of the Z axis by a certain thickness , forming a ring-belt structure with a thickness; then according to the number of microstrip antennas in the transmitting antenna determined , the annular array is formed A circularly distributed arc-shaped microstrip antenna; Along the positive direction of the Z axis and at a distance from the XOY plane The first PCB substrate is constructed in the second bias plane, and the arc-shaped microstrip antenna is fed through the coaxial line.

4. A system for designing parameters of variable-range telemetry antennas for aircraft engines, used to implement the design method described in claim 1; characterized in that: include: A data acquisition module, used to determine the number of microstrip antennas in the transmitting antenna according to the number of measuring points of the aircraft engine rotor; The first analysis module is used to analyze and obtain the length of the arc microstrip antenna using a rectangular microstrip antenna length calculation method according to the width design value of the transmitting antenna, the first PCB substrate design specification parameters of the transmitting antenna, and the target resonant frequency of the variable-range telemetry antenna, and to analyze and obtain the curvature of each microstrip antenna according to the number of microstrip antennas. ,in The length of the arc microstrip antenna is obtained by using the rectangular microstrip antenna length calculation method. , is the number of microstrip antennas in the transmitting antenna, For data value The ceiling function of ; A simulation model building module, used to build a receiving antenna simulation model based on a second PCB substrate and a non-closed circular ring structure by taking the width design value of the transmitting antenna as the width of the receiving antenna; And according to the number of microstrip antennas, the width design value of the transmitting antenna, and the curvature of each microstrip antenna, a transmitting antenna simulation model based on the first PCB substrate and the microstrip antenna is constructed; A simulation analysis module is used to solve the transmission coefficient change curve of the variable-range telemetry antenna based on the transmitting antenna simulation model and the receiving antenna simulation model by mode driving under different spacing values ​​and different resonant frequency combinations between the transmitting antenna simulation model and the receiving antenna simulation model with an air box of not less than 1 / 4 wavelength as a radiation boundary condition; The parameter determination module is used to determine the resonant frequency range and the corresponding spacing value range that are not less than the preset transmission coefficient threshold in the transmission coefficient change curve, which are used as the working frequency band and the switching spacing working range of the variable-range telemetry antenna respectively.

5. The design system according to claim 4, characterized in that: In the simulation model construction module, a method for constructing a receiving antenna simulation model based on a second PCB substrate and a non-closed circular ring structure includes: Take any point O in space as the origin and establish a Cartesian coordinate system O-XYZ; Construct a non-closed circular line in the XOY plane with the origin O as the center ,in is the angle range of the non-closed circular line, The value range is , is the annular angle of the non-closed circular ring structure, is the coordinate value of the non-closed circular line on the X-axis, is the coordinate value of the non-closed circular line on the Y axis, is the coordinate value of the non-closed circular line on the Z axis; In the XOY plane, the non-closed loop line is offset inwards and outwards respectively. , and connect the corresponding end points to form an arc-shaped belt; is the width of the receiving antenna; The arc-shaped belt is offset along the positive direction of the Z axis by a certain thickness , forming a non-closed circular loop antenna structure with thickness; The second PCB substrate is constructed in a plane along the negative direction of the Z axis and parallel to XOY; and one end of the non-closed circular loop antenna structure is grounded through a radio frequency resistor.

6. The design system according to claim 5, characterized in that: In the simulation model construction module, a method for constructing a simulation model of a transmitting antenna based on a first PCB substrate and a microstrip antenna includes: Along the positive direction of the Z axis and at a distance from the XOY plane The first arc line is constructed in the first offset plane ,in is the angle range of the first arc line, The value range is , is the arc of the microstrip antenna, is the coordinate value of the first arc line on the X-axis, is the coordinate value of the first arc line on the Y axis, is the coordinate value of the first arc line on the Z axis, It is the distance between the rotor and the static of the aircraft engine; In the first offset plane, the first arc line is offset inward and outward respectively. , and connect the corresponding endpoints to form a ring structure; Design value for the width of the transmitting antenna; The ring belt structure is offset along the positive direction of the Z axis by a certain thickness , forming a ring-belt structure with a thickness; then according to the number of microstrip antennas in the transmitting antenna determined , the annular array is formed A circularly distributed arc-shaped microstrip antenna; Along the positive direction of the Z axis and at a distance from the XOY plane The first PCB substrate is constructed in the second bias plane, and the arc-shaped microstrip antenna is fed through the coaxial line.

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