CN215893640U - Follow-up probe system with rotor wing downwash influence correction function - Google Patents
Follow-up probe system with rotor wing downwash influence correction function Download PDFInfo
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- CN215893640U CN215893640U CN202121390894.1U CN202121390894U CN215893640U CN 215893640 U CN215893640 U CN 215893640U CN 202121390894 U CN202121390894 U CN 202121390894U CN 215893640 U CN215893640 U CN 215893640U
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Abstract
The follow-up probe system with rotor wing down-wash influence correction comprises a support arm, a differential pressure probe arranged on the support arm, a static temperature sensor arranged on the support arm and a follow-up probe arranged on the support arm, wherein the differential pressure probe, the static temperature sensor and the follow-up probe are respectively connected to an external processing module; the side surface of the differential pressure probe is provided with a plurality of static pressure holes; the follow-up probe comprises a follow-up airspeed head and a rotating part, the follow-up airspeed head is rotatably connected to the rotating part, and the rotating part is connected to the support arm. The scheme integrates the total static pressure probe and the static temperature sensor which are separated from the traditional helicopter air data system into an integrated air data system, can provide the output of an attack angle and a sideslip angle, and obviously improves the system integration degree; the follow-up probe has the capability of following the direction of the airflow in real time, so that the accuracy of total pressure and static pressure feeling of the probe is improved; the rotor wing downwash flow correction function is achieved, and the measurement performance of the atmospheric data system is improved.
Description
Technical Field
The utility model relates to the field of atmospheric data, in particular to a follow-up probe system with rotor wing downwash influence correction function.
Background
The civil helicopter atmospheric data system is a system or equipment for measuring parameters such as the flight altitude, the speed, the total temperature/static temperature, the attack angle, the sideslip angle and the like of a helicopter in real time by utilizing the principle of measuring barometric pressure, namely total pressure and static pressure, and is an important system influencing the flight safety and navigation display of the helicopter. The failure of the atmospheric data system can cause the failure of the airplane, belongs to safety key equipment of the helicopter, and the development guarantee level is DAL A level, namely the highest level. Therefore, accurate measurement of atmospheric parameters of the civil helicopter atmospheric data system is of great importance to helicopter flight safety.
The civil helicopter atmospheric data system generally adopts a fixed total static pressure probe or a total pressure and fuselage static pressure hole to realize the feeling of the total pressure and the static pressure of the helicopter, and the calculation of the barometric altitude, the indication airspeed, the Mach number, the indication airspeed, the vacuum speed and the like is finished according to the total pressure and the static pressure which are collected, so the accurate feeling and measurement of the total pressure and the static pressure are the basis and the premise for ensuring the measurement precision of the atmospheric data system.
The traditional helicopter air data system mainly comprises a separated fixed total static pressure probe, a static temperature sensor and an air data computer, wherein the helicopter is powered and lifted by a rotor wing, and downwash airflow is generated below the rotor wing when the helicopter flies. Due to the special aerodynamic characteristics of the helicopter, an air data probe arranged on a helicopter body is inevitably influenced by induced airflow of a helicopter rotor wing when the helicopter flies at a low speed, and a traditional helicopter air data system does not consider the influence of rotor wing downwash, directly adopts a fixed-wing aircraft air data system measurement technology, has inherent technical defects, causes inaccurate air data measurement and influences the flight safety of the helicopter.
SUMMERY OF THE UTILITY MODEL
The utility model aims to: the follow-up probe system with the rotor wing downwash influence correction function can provide output of an attack angle and a sideslip angle, the follow-up probe has the capability of following the direction of airflow in real time, accuracy of total pressure and static pressure sensing of the probe is improved, the insensitive angle range of the probe is reduced, measurement performance of an atmospheric data system is improved, and the problems are solved.
The technical scheme adopted by the utility model is as follows:
the follow-up probe system with rotor wing down-wash influence correction comprises a support arm, a processing module arranged in the support arm, a differential pressure probe arranged on the support arm, a static temperature sensor arranged on the support arm and a follow-up probe arranged on the support arm, wherein the differential pressure probe, the static temperature sensor and the follow-up probe are respectively connected to the processing module;
the side surface of the differential pressure probe is provided with a plurality of static pressure holes for measuring static pressure;
follow-up probe includes follow-up airspeed head and rotation portion, follow-up airspeed head rotates and is connected to rotation portion, rotation portion connects on the support arm.
In order to better implement the scheme, further, the follow-up probe is based on a three-axis rotating structure or a universal joint rotating structure.
In order to better realize the scheme, the rotation angle range of the follow-up airspeed tube along the horizontal direction is-180 degrees, and the rotation angle range of the follow-up airspeed tube along the vertical direction is-40 degrees.
In order to better realize the scheme, the static pressure holes are further symmetrically distributed along the circumference of the side surface of the differential pressure probe.
In order to better realize the scheme, the number of the static pressure holes is further 4-6.
In summary, due to the adoption of the technical scheme, the utility model has the beneficial effects that:
1. the atmospheric data system with rotor wing down-wash influence correction integrates the total static pressure probe and the static temperature sensor which are separated in the conventional helicopter atmospheric data system into an integrated atmospheric data system, can provide output of an attack angle and a sideslip angle, and remarkably improves the comprehensive degree, reliability, maintainability, volume, weight and other performances of the system;
2. according to the atmospheric data system with rotor wing downwash influence correction, the follow-up probe has the capability of following the direction of the airflow in real time, the accuracy of total pressure and static pressure feeling of the probe is improved, and the insensitive angle range of the probe is reduced;
3. the atmospheric data system with rotor wing downwash influence correction has the rotor wing downwash correction function, and the measurement performance of the atmospheric data system is improved.
Drawings
In order to more clearly illustrate the technical solution, the drawings needed to be used in the embodiments are briefly described below, and it should be understood that, for those skilled in the art, other related drawings can be obtained according to the drawings without creative efforts, wherein:
FIG. 1 is a schematic diagram of an air data system based on a three-axis rotating structure according to the present invention;
FIG. 2 is a schematic diagram of a three-axis rotary structure-based servo probe structure of the present invention;
FIG. 3 is a schematic diagram of an atmospheric data system architecture based on a gimbal rotating architecture of the present invention;
FIG. 4 is a schematic diagram of a structure of a servo probe based on a universal joint rotating structure;
FIG. 5 is a schematic illustration of a differential pressure probe of the present invention with 6 and 4 static pressure port openings;
FIG. 6 is a schematic diagram of the differential pressure probe, the static temperature sensor and the follower probe of the present invention connected to a processing module respectively.
Detailed Description
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it should be understood that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments, and therefore should not be considered as a limitation to the scope of protection. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "disposed," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
The present invention will be described in detail with reference to fig. 1 to 6.
Example 1:
the follow-up probe system with rotor wing down-wash influence correction, as shown in fig. 1 or fig. 3, comprises a support arm, a processing module arranged in the support arm, a differential pressure probe arranged on the support arm, a static temperature sensor arranged on the support arm and a follow-up probe arranged on the support arm, as shown in fig. 6, wherein the differential pressure probe, the static temperature sensor and the follow-up probe are respectively connected to the processing module, and the internal structure of the processing module is as shown in fig. 6;
the side surface of the differential pressure probe is provided with a plurality of static pressure holes for measuring static pressure;
follow-up probe includes follow-up airspeed head and rotation portion, follow-up airspeed head rotates and is connected to rotation portion, rotation portion connects on the support arm.
The working principle is as follows: the scheme realizes the rotation of the total static pressure probe, realizes the follow-up function of the total static pressure probe, and enables the total pressure measuring port of the total pressure measuring port to be always aligned with the airflow direction and the static pressure hole to be perpendicular to the synthetic airflow, thereby ensuring the accuracy of static pressure measurement, and meanwhile, the total pressure hole is always felt by the synthesis of total pressure, and the association between the synthesis of total pressure and the rotor wing wash-down flow is completed. And establishing a rotor wing downwash influence correction model through rotor wing downwash influence and combined total pressure, pressure difference probe static pressure hole and other pressure change rules, so that the rotor wing downwash influence correction function is realized.
The correction model in the atmospheric data correction method with rotor downwash influence correction is as follows:
pt = Pti +. DELTA.Pt, where Pt is the true total pressure, Pti is the total pressure measurement, and DELTA.Pt is the total pressure correction value under the influence of the rotor wash-down;
ps = Psi plus Δ Ps, where Ps is a real static pressure, Psi is a static pressure measurement value, and Δ Ps is a static pressure correction value under the influence of rotor downwash;
Δ Pt = F1[ Pti, Psi, (Pu-Pd), (Pl-Pr) ], where F1 is a total pressure correction function established according to the left-right differential pressure and the up-down differential pressure of the differential pressure probe, Pl-Pr is a left-right differential pressure measurement value of the differential pressure probe, and Pu-Pd is an up-down differential pressure measurement value of the differential pressure probe;
Δ Ps = F2[ (Pti, Psi, (Pu-Pd), (Pl-Pr) ], where F2 is a static pressure correction function established from the differential pressure probe for the left-right differential pressure and the differential pressure for the upper-lower differential pressure.
When the static pressure holes of the differential pressure probe are 6, correcting delta Pt = F1[ Pti, Psi, (P1-P4), (P2-P5), (P3-P6) ], delta Ps = F2[ Pti, Psi, (P1-P4), (P2-P5), (P3-P6) ], wherein P1-P4 is the differential pressure measurement value of the static pressure holes Pk1 and Pk4 of the differential pressure probe; P2-P5 are pressure difference measurement values of static pressure holes Pk2 and Pk5 of the pressure difference probe; P3-P6 are pressure difference measurement values of the static pressure holes Pk3 and Pk6 of the pressure difference probe, and Pk1, Pk2, Pk3, Pk4, Pk5 and Pk6 are 6 static pressure holes distributed in sequence.
Example 2:
the scheme is based on the embodiment 1, and the follow-up probe is based on a three-axis rotating structure as shown in fig. 2 or a universal joint rotating structure as shown in fig. 4. The external processing module is arranged in the support arm.
The rotation angle range of the follow-up airspeed tube along the horizontal direction is-180 degrees to 180 degrees, and the rotation angle range of the follow-up airspeed tube along the vertical direction is-40 degrees to 40 degrees. The static pressure holes are symmetrically distributed along the circumference of the side surface of the differential pressure probe. As shown in FIG. 5, the number of static pressure holes is 4 to 6.
The working principle is as follows: as shown in fig. 2, the rotation function of the total static pressure probe is realized through a triaxial rotation structure, the follow-up function of the total static pressure probe is realized through the vane aerodynamic moment on the follow-up probe, so that the total pressure measuring port of the total static pressure probe is always aligned to the airflow direction, and the static pressure holes are perpendicular to the synthetic airflow, thereby ensuring the accuracy of static pressure measurement. The present embodiment then establishes a correlation between rotor downwash and the change in hydrostatic-bore pressure by uniformly opening 4 or 6 hydrostatic bores in the differential pressure probe. And establishing a rotor wing downwash influence correction model through rotor wing downwash influence and combined total pressure, pressure difference probe static pressure hole and other pressure change rules, so that the rotor wing downwash influence correction function is realized.
The rotating function of the total static pressure probe is realized by adopting a universal joint rotating structure as shown in fig. 4, the following function of the total static pressure probe is realized by the vane aerodynamic moment on the following probe, so that the total pressure measuring port of the total pressure probe is always aligned to the airflow direction, and the static pressure hole is perpendicular to the synthetic airflow, thereby ensuring the accuracy of static pressure measurement. In the embodiment, 4 or 6 static pressure holes are uniformly formed in the straight rod of the probe, so that the correlation between the rotor wing downward washing flow and the pressure change of the static pressure holes is established. According to the embodiment, a rotor wing downwash influence correction model is established through the rotor wing downwash influence and the combined total pressure and the pressure change rule such as a probe straight rod static hole, so that the rotor wing downwash influence correction function is realized.
Other parts of this embodiment are the same as those of embodiment 1, and thus are not described again.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention in any way, and all simple modifications and equivalent variations of the above embodiments according to the technical spirit of the present invention are included in the scope of the present invention.
Claims (5)
1. Follow-up probe system with rotor downwash influence is revised, its characterized in that: the device comprises a support arm, a processing module arranged in the support arm, a differential pressure probe arranged on the support arm, a static temperature sensor arranged on the support arm and a follow-up probe arranged on the support arm, wherein the differential pressure probe, the static temperature sensor and the follow-up probe are respectively connected to the processing module;
the side surface of the differential pressure probe is provided with a plurality of static pressure holes for measuring static pressure;
follow-up probe includes follow-up airspeed head and rotation portion, follow-up airspeed head rotates and is connected to rotation portion, rotation portion connects on the support arm.
2. The follow-up probe system with rotor downwash effect correction as recited in claim 1, wherein: the follow-up probe is based on a three-axis rotating structure or a universal joint rotating structure.
3. The follow-up probe system with rotor downwash effect correction as recited in claim 1, wherein: the rotation angle range of the follow-up airspeed tube along the horizontal direction is-180 degrees to 180 degrees, and the rotation angle range of the follow-up airspeed tube along the vertical direction is-40 degrees to 40 degrees.
4. The follow-up probe system with rotor downwash effect correction as recited in claim 1, wherein: the static pressure holes are symmetrically distributed along the circumference of the side surface of the differential pressure probe.
5. The follow-up probe system with rotor downwash effect correction as recited in claim 1, wherein: the number of the static pressure holes is 4-6.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202121390894.1U CN215893640U (en) | 2021-06-22 | 2021-06-22 | Follow-up probe system with rotor wing downwash influence correction function |
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| CN202121390894.1U CN215893640U (en) | 2021-06-22 | 2021-06-22 | Follow-up probe system with rotor wing downwash influence correction function |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113624393A (en) * | 2021-06-22 | 2021-11-09 | 成都凯天电子股份有限公司 | Atmospheric data system and method with rotor downwash effect correction |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113624393A (en) * | 2021-06-22 | 2021-11-09 | 成都凯天电子股份有限公司 | Atmospheric data system and method with rotor downwash effect correction |
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