Aircraft flight test response measurement integrated device for a test and control equipment

Abstract

The utility model provides a kind of measuring and controlling equipment airplane school flies response measurement integrated device, it is related to spaceflight measuring and controlling technical field, as multiple measuring and controlling cooperation target is set on school flies airplane platform, wherein, Ka band comprehensive measuring and controlling terminal, multi-frequency continuous wave transponder, and power inverter are installed on airplane rear seat;Pulse phase reference transponder, double-frequency continuous wave transponder, USB transponder, frequency converter and duplexer are installed in rear luggage compartment;C band pulse phase reference antenna, double-frequency continuous wave transmitting antenna and receiving antenna, Ka band antenna, USB transmitting antenna and receiving antenna, multi-frequency continuous wave transmitting antenna and receiving antenna are set in the sling pod under airplane belly.The utility model carries out modification and electromagnetic compatibility analysis to school flies airplane platform, realizes the electromagnetic compatibility of measuring and controlling cooperation target covering C, S, X, Ka each frequency band, work simultaneously, can effectively support the organization implementation of school flies.

Description

Technical Field

[0001] This utility model relates to the field of aerospace measurement and control technology, and more specifically, to an integrated measurement and control device for aircraft flight calibration response. Background Technology

[0002] To verify the tracking performance and measurement accuracy of the telemetry and control equipment, it is necessary to use manned or unmanned aircraft to carry the telemetry and control cooperation target and conduct calibration flights within a limited airspace. The telemetry and control cooperation target mainly consists of a transponder and an antenna, which need to be integrated and installed on the calibration aircraft platform. On the one hand, it is necessary to conduct necessary strength analysis and weight and center of gravity impact assessments; on the other hand, it is necessary to optimize the arrangement of antennas in each frequency band. Utility Model Content

[0003] The purpose of this invention is to solve the problems of integrated installation and electromagnetic compatibility of telemetry and control cooperative targets within a limited space on a calibration aircraft platform.

[0004] Therefore, this utility model provides an integrated measurement and control device for aircraft calibration flight test response, which is set on the calibration aircraft platform as multiple measurement and control cooperative targets. The integrated device includes: a C-band pulse coherent antenna and a corresponding pulse coherent transponder; a dual-frequency continuous wave transmitting antenna and a receiving antenna and a corresponding dual-frequency continuous wave transponder; a Ka-band antenna and a Ka-band integrated measurement and control terminal; a USB transmitting antenna and a receiving antenna and a corresponding USB transponder; a multi-frequency continuous wave transmitting antenna and a receiving antenna and a corresponding multi-frequency continuous wave transponder; a power inverter; a frequency converter; and a duplexer.

[0005] The Ka-band integrated telemetry and control terminal, multi-frequency continuous wave transponder, and power inverter are installed on the rear seats of the aircraft.

[0006] Pulse coherent transponders, dual-frequency continuous wave transponders, USB transponders, frequency converters, and duplexers are installed in the rear baggage compartment of the aircraft;

[0007] The C-band pulse coherent antenna, dual-frequency continuous wave transmitting and receiving antenna, Ka-band antenna, USB transmitting and receiving antenna, and multi-frequency continuous wave transmitting and receiving antenna are installed in a pod under the fuselage of the aircraft.

[0008] Furthermore, the C-band pulse coherent antenna is located in the middle of the pod; the dual-frequency continuous wave transmitting and receiving antennas, the USB transmitting and receiving antennas, and the multi-frequency continuous wave transmitting and receiving antennas are symmetrically arranged at the edge of the pod, and the dual-frequency continuous wave antenna, the USB antenna, and the multi-frequency continuous wave antenna are all spaced apart by a predetermined distance; the Ka-band antenna is located at the edge of the pod and between the dual-frequency continuous wave transmitting antenna and the USB transmitting antenna.

[0009] Furthermore, the isolation between multiple antennas meets electromagnetic compatibility requirements.

[0010] Furthermore, the integrated device also includes: absorbing material of the corresponding frequency band installed on parts of the machine body that may generate strong electromagnetic reflections.

[0011] Furthermore, the integrated device also includes a harmonic filter for removing pulse harmonics.

[0012] Furthermore, the data collected by the integrated device is uploaded to the data analysis center after being unloaded on the ground.

[0013] Furthermore, multiple ground-based telemetry and control devices corresponding to multiple cooperative targets include: C-band pulse radar, dual-frequency continuous wave radar, Ka-band measurement equipment, USB devices, and multi-frequency continuous wave radar.

[0014] This invention modifies and analyzes the electromagnetic compatibility of a calibration flight aircraft platform, and designs a method for installing measurement and control cooperation targets on the calibration flight aircraft platform that integrates multiple systems such as C-band pulse coherence, dual-frequency continuous wave, Ka-band integrated measurement and control, USB, and multi-frequency continuous wave. It achieves electromagnetic compatibility and simultaneous operation of measurement and control cooperation targets covering C, S, X, and Ka frequency bands, and can effectively support the organization and implementation of calibration flights. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the main information flow of the calibration flight process of this utility model;

[0016] Figure 2 This is a schematic diagram of the equipment installation layout of this utility model;

[0017] Figure 3 This is a layout diagram of the fuselage adapter structure of this utility model;

[0018] Figure 4 This is a layout diagram of the antenna positions for different frequency bands of this utility model. Detailed Implementation

[0019] The present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present invention and are not intended to limit the present invention.

[0020] 1. Aircraft installation plan

[0021] The calibration aircraft, after modifications, carried five telemetry and control cooperative targets and flew in designated airspace, cooperating with ground telemetry and control equipment to complete the calibration flight. Its main information flow is as follows: Figure 1As shown. To meet the integration and installation requirements of different telemetry and control cooperation targets during the flight calibration of the telemetry and control equipment, based on necessary strength analysis and weight and center of gravity impact assessments of the design scheme, the designed installation layout of the transponder for the telemetry and control cooperation targets is as follows. Figure 2 As shown. To reduce the impact of the aircraft on the target antenna for telemetry and control cooperation, it is necessary to install absorbing materials of the corresponding frequency band on the parts of the aircraft that may generate strong electromagnetic reflections to weaken their impact on the antenna pattern.

[0022] 2. Electromagnetic Compatibility Solution

[0023] Multiple sets of telemetry and control target antennas are integrated and installed in, for example Figure 3 On the aircraft platform's belly-mounted transition structure shown, the antennas operate at different frequencies. Since aircraft are mostly composed of metal components, these components can affect the propagation of electromagnetic waves, causing distortion in the antenna pattern. Therefore, electromagnetic compatibility must be considered in the design of multi-band antennas. Figure 4 As shown, the C-band pulse coherent, dual-frequency continuous wave, Ka-band integrated telemetry and control, USB, and multi-frequency continuous wave antennas achieve high isolation between antennas through reasonable optimization of their layout within the fuselage, thus meeting the system's electromagnetic compatibility requirements. Furthermore, harmonic filters can be added to remove interference from pulse harmonics between various types of telemetry and control target antennas.

[0024] 3. Ground docking plan and verification

[0025] To mitigate risks related to the normal operation and electromagnetic compatibility of the integrated telemetry and control (TT&C) equipment after installation, a docking test was conducted. The main tasks included: checking the interface compatibility between the transceiver antennas and the transponders; verifying the normal operation of the transponders and other equipment; checking the electromagnetic compatibility of the transponder signals during joint startup; and verifying parameters such as the transponder attenuator settings. The integrated flight calibration ground docking test demonstrated that the transponders and ground TT&C equipment functioned normally. All transponders, attenuators, and airborne antennas were properly connected and their interfaces were compatible. No interference signals affecting signal transmission and reception were detected, and the system demonstrated electromagnetic compatibility.

[0026] The above embodiments are only used to illustrate the technical solution of this utility model and not to limit it. Although the utility model has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications can still be made to the specific implementation of this utility model or equivalent substitutions can be made to some technical features without departing from the spirit of the technical solution of this utility model, and all such modifications and substitutions should be covered within the scope of the technical solution claimed by this utility model.

Claims

1. A measurement and control equipment aircraft calibration response measurement integration device, which is set on a calibration aircraft platform as multiple measurement and control cooperation targets, characterized in that, The integrated device includes: a C-band pulse coherent antenna and a corresponding pulse coherent transponder, a dual-frequency continuous wave transmitting antenna and a receiving antenna and a corresponding dual-frequency continuous wave transponder, a Ka-band antenna and a Ka-band integrated measurement and control terminal, a USB transmitting antenna and a receiving antenna and a corresponding USB transponder, a multi-frequency continuous wave transmitting antenna and a receiving antenna and a corresponding multi-frequency continuous wave transponder, a power inverter, a frequency converter, and a duplexer; among which... The Ka-band integrated telemetry and control terminal, multi-frequency continuous wave transponder, and power inverter are installed on the rear seats of the aircraft. Pulse coherent transponders, dual-frequency continuous wave transponders, USB transponders, frequency converters, and duplexers are installed in the rear baggage compartment of the aircraft. The C-band pulse coherent antenna, dual-frequency continuous wave transmitting and receiving antenna, Ka-band antenna, USB transmitting and receiving antenna, and multi-frequency continuous wave transmitting and receiving antenna are installed in a pod under the fuselage of the aircraft.

2. The integrated device of claim 1, wherein, The C-band pulse coherent antenna is located in the middle of the pod; the dual-frequency continuous wave transmitting and receiving antennas, the USB transmitting and receiving antennas, and the multi-frequency continuous wave transmitting and receiving antennas are symmetrically arranged at the edge of the pod, and the dual-frequency continuous wave antenna, the USB antenna, and the multi-frequency continuous wave antenna are all spaced at a predetermined distance; the Ka-band antenna is located at the edge of the pod and between the dual-frequency continuous wave transmitting antenna and the USB transmitting antenna.

3. The integrated device of claim 2, wherein, The isolation between multiple antennas meets electromagnetic compatibility requirements.

4. The integrated device of claim 1, wherein, The integrated device also includes: absorbing materials for the corresponding frequency band that are installed on parts of the machine body that may generate strong electromagnetic reflections.

5. The integrated device of claim 1, wherein, The integrated device also includes a harmonic filter for removing pulse harmonics.

6. The integrated device of claim 1, wherein, The data collected by the integrated device is uploaded to the data analysis center after being unloaded on the ground.

7. The integrated device of claim 1, wherein, Multiple ground-based telemetry and control equipment corresponding to various cooperative targets include: C-band pulse radar, dual-frequency continuous wave radar, Ka-band measurement equipment, USB devices, and multi-frequency continuous wave radar.

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