Height measurement antenna device adaptive to maneuvering action of aircraft

Abstract

The invention provides a height measurement antenna device adapted to maneuvering actions of an aircraft. The height measurement antenna device comprises an altimeter, an antenna switch, an attitude sensing and control unit, and multiple groups of receiving antennas and transmitting antennas, the altimeter is mounted on the surface of the aircraft; the outer side ends of the receiving antennas and the transmitting antennas are installed on the surface of the aircraft at intervals according to a preset aircraft roll angle. The inner side ends of the plurality of groups of receiving antennas and the transmitting antenna are connected with an antenna switch arranged in the altimeter; the attitude sensing and control unit is connected with the antenna switch; when the attitude of the aircraft changes, the attitude sensing and control unit can adjust the antenna switch, and the receiving antenna and the transmitting antenna corresponding to the current aircraft roll angle are switched. The system provided by the invention is simple in structure, easy to realize, high in reliability and low in maintenance cost, and can effectively expand the attitude adaptability of the radio altimeter to the strong maneuvering aircraft.

Description

Technical Field

[0001] The present invention belongs to the technical field of radar navigation. Specifically, it relates to an altimeter antenna device adapted to the maneuvering actions of an aircraft. More specifically, it is an altimeter antenna system for a highly maneuverable aircraft. Background Art

[0002] A radio altimeter is a commonly used aviation device for measuring the vertical distance between an aircraft and the ground or sea surface. Radio altimeters with a maximum range of less than 1500 m usually adopt a frequency modulation continuous wave system.

[0003] A radio altimeter generally consists of a transceiver, a transmitting antenna, a receiving antenna, a transmitting cable, and a receiving cable.

[0004] The basic principle block diagram of a radio altimeter is as Figure 1 shown. To adapt to the movement of the altimeter carrier, the altimeter antenna needs to have a certain beam width. According to the radio frequency division, the operating frequency of the altimeter is 4.2 - 4.4 GHz. Usually, altimeters in this frequency band adopt a four-element choke microstrip antenna, and its beam width is usually about ±35°, which can meet the requirements of the roll angle of the carrier under normal circumstances. Currently, some altimeters have adopted the millimeter wave band. Since the equivalent aperture of the millimeter wave band antenna is smaller, in order to obtain better antenna gain in the millimeter wave band, its antenna beam is narrower and its adaptability to the carrier is worse.

[0005] Patent document CN115508818B discloses a radio altimeter analog altimetry device, which is used to solve the problem of poor radio altimeter test technology in related technologies. In this device, the stroke amplification pulley group includes a movable pulley group and a fixed pulley group for the hoisting rope for hoisting the altimeter mounting plate. The movable pulley group and the fixed pulley group can amplify the relative displacement between the movable pulley group and the fixed pulley group into several times the traction distance of the hoisting rope. The slide of the lead screw slide mechanism drives the connecting movable pulley group. The rotation drive mechanism is used to drive the lead screw of the lead screw slide mechanism to rotate. The position detection module is used to detect the position of the slide on the lead screw. The control module receives the ranging result of the altimeter to be tested and the position result of the slide on the lead screw. The control module calculates the height between the radio altimeter and the ground according to the position of the slide, and compares it with the ranging result of the radio altimeter to determine the test accuracy of the radio altimeter. This solution cannot improve the adaptability to different carriers, and has a complex structure, increasing the maintenance cost.

[0006] Patent document CN213581337U discloses a patent for a Ka-band millimeter-wave radar, which uses two millimeter-wave altimeters. A relatively large antenna beam width is obtained through two sets of orthogonally arranged antennas. In essence, it is the collaborative work of two independent millimeter-wave altimeters to achieve the purpose, and the adaptability to the carrier does not exceed the requirement of a roll angle of ±35°, and the cost is increased. And it is not applicable to the requirements of the 4.2 - 4.4 GHz frequency band.

[0007] During the flight of some aircraft that need to maneuver, their roll angles usually far exceed the range of ±35°, and even reach ±90°. In such unconventional maneuvering flights, conventional radio altimeters cannot meet their requirements.

[0008] Currently, there are several methods to solve the above problems:

[0009] First, increase the antenna beam, but this method will seriously reduce the antenna gain, thereby reducing the sensitivity of the altimeter, reducing the high-performance measurement of the altimeter, and introducing stronger interference signals after the antenna beam is increased, further deteriorating the performance of the altimeter.

[0010] Second, use multiple altimeters to work simultaneously, each adapting to different attitude angles, but this method will increase the cost, and the simultaneous operation of multiple altimeters will bring co-frequency asynchronous interference, affecting the altitude measurement of the altimeter. Summary of the Invention

[0011] Aiming at the defects in the prior art, the purpose of the present invention is to provide an altitude measurement antenna device adapted to the maneuvering actions of an aircraft.

[0012] An altitude measurement antenna device adapted to the maneuvering actions of an aircraft according to the present invention includes: an altimeter, an antenna switch, an attitude sensing and control unit, multiple sets of receiving antennas and transmitting antennas; the altimeter is installed on the surface of the aircraft; the outer ends of multiple sets of the receiving antennas and transmitting antennas are respectively installed on the surface of the aircraft at intervals according to a preset roll angle of the aircraft; the inner ends of multiple sets of the receiving antennas and transmitting antennas are connected and installed to the antenna switch inside the altimeter; the attitude sensing and control unit is connected to the antenna switch;

[0013] When the attitude of the aircraft changes, the attitude sensing and control unit can adjust the antenna switch to switch the receiving antennas and transmitting antennas corresponding to the current roll angle of the aircraft.

[0014] Preferably, the angles of the preset roll angle of the aircraft are 0°, +60° and -60° respectively.

[0015] Preferably, the attitude sensing and control unit includes: a gyroscope and a signal processing unit;

[0016] The signal processing unit can receive the roll angle of the gyroscope, and then control the corresponding antenna switch according to the roll angle.

[0017] Preferably, it includes: three groups of receiving antennas and transmitting antennas; the three groups of receiving antennas and transmitting antennas include: a first receiving antenna, a first transmitting antenna, a second receiving antenna, a second transmitting antenna, a third receiving antenna and a third transmitting antenna;

[0018] The outer ends of the first receiving antenna, the second receiving antenna and the third receiving antenna are respectively installed on one side of the lower surface of the aircraft when the roll angle of the aircraft is 0°, +60°, -60°; the outer ends of the first transmitting antenna, the second transmitting antenna and the third transmitting antenna are respectively installed on the other side of the lower surface of the aircraft when the roll angle of the aircraft is 0°, +60°, -60°; the inner ends of the first receiving antenna, the second receiving antenna and the third receiving antenna are connected to the altimeter; the inner ends of the first transmitting antenna, the second transmitting antenna and the third transmitting antenna are connected to the altimeter.

[0019] Preferably, the antenna switch includes a radio frequency switch or an electronic switch; the radio frequency switch is connected to the signal processing unit; the electronic switch is connected to the signal processing unit.

[0020] Preferably, the antenna switch is a double-pole triple-throw switch; the double-pole triple-throw switch can receive the signal of the signal processing unit and switch to the transmitting antenna and receiving antenna corresponding to the signal.

[0021] Preferably, the signal processing unit can receive the signal of the altimeter and output the current altitude information.

[0022] Preferably, the gyroscope is installed inside the aircraft.

[0023] Preferably, it further includes: a signal amplifier; the signal amplifier is connected to the signal processing unit; the signal amplifier is connected to the double-pole triple-throw switch.

[0024] Preferably, the double-pole triple-throw switch can receive the signal of the receiving antenna and send it to the signal processing unit.

[0025] Compared with the prior art, the present invention has the following beneficial effects:

[0026] 1. The system provided by the present invention has a simple structure, is easy to implement, has high reliability and low maintenance cost.

[0027] 2. The present invention can effectively expand the attitude adaptability of the radio altimeter to maneuvering aircraft.

[0028] 3. The outer ends of multiple groups of the receiving antennas and transmitting antennas provided by the present invention are respectively installed on the surface of the aircraft at intervals according to a preset roll angle of the aircraft, which can meet the adaptive requirements for the roll angle of a maneuvering aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Other features, objects, and advantages of the present invention will become more apparent by reading the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0030] Figure 1 It is a simplest principle block diagram of a radio altimeter;

[0031] Figure 2 It is a schematic block diagram of the system principle provided by the present invention;

[0032] Figure 3 It is a three-dimensional schematic diagram of the hardware structure provided by the present invention;

[0033] Figure 4 It is a top view schematic diagram of the hardware structure provided by the present invention;

[0034] Figure 5 It is a principle block diagram of the radio altimeter provided by the present invention.

[0035] The figures show:

[0036] 1 - First transmitting antenna 5 - First receiving antenna

[0037] 2 - Second transmitting antenna 6 - Second receiving antenna

[0038] 3 - Third transmitting antenna 7 - Third receiving antenna

[0039] 4 - Altimeter host 8 - Aircraft DETAILED DESCRIPTION OF THE EMBODIMENTS

[0040] The present invention will be described in detail below with reference to specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that those of ordinary skill in the art can make several changes and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0041] The technical problems to be solved by the present invention are reflected in the following aspects: First, maintain the operating frequency of the altimeter at 4200 - 4400 MHz to make it have wide applicability. Second, ensure that one altimeter host can meet the requirements of a highly maneuverable aircraft to reduce costs.

[0042] To solve the above technical problems, a height measurement antenna device adapted to the maneuvering actions of an aircraft provided by the present invention includes:

[0043] The altimeter altitude measurement part is used for conventional radio altitude measurement;

[0044] Attitude sensing and control are used to sense the roll angle attitude of the aircraft;

[0045] The double - pole triple - throw switch is used to synchronously switch the altimeter transmitting antenna and receiving antenna under the control of the attitude sensing and control part;

[0046] Transmitting antenna 1, that is, the first transmitting antenna, is used to transmit the altimeter radio frequency signal;

[0047] Transmitting antenna 2, that is, the second transmitting antenna, is used to transmit the altimeter radio frequency signal;

[0048] Transmitting antenna 3, that is, the third transmitting antenna, is used to transmit the altimeter radio frequency signal;

[0049] Receiving antenna 1, that is, the first receiving antenna, is used to receive the altimeter radio frequency signal;

[0050] Receiving antenna 2, that is, the second receiving antenna, is used to receive the altimeter radio frequency signal;

[0051] Receiving antenna 3, that is, the third receiving antenna, is used to receive the altimeter radio frequency signal;

[0052] In other words, there are three groups of receiving antennas and transmitting antennas, including: the first receiving antenna, the first transmitting antenna, the second receiving antenna, the second transmitting antenna, the third receiving antenna and the third transmitting antenna;

[0053] Specifically, the outer ends of the first receiving antenna, the second receiving antenna and the third receiving antenna are respectively installed on one side of the lower surface of the aircraft when the roll angle of the aircraft is 0°, +60°, -60°; the outer ends of the first transmitting antenna, the second transmitting antenna and the third transmitting antenna are respectively installed on the other side of the lower surface of the aircraft when the roll angle of the aircraft is 0°, +60°, -60°; the inner ends of the first receiving antenna, the second receiving antenna and the third receiving antenna are connected to the altimeter; the inner ends of the first transmitting antenna, the second transmitting antenna and the third transmitting antenna are connected to the altimeter.

[0054] Specifically, the antenna switch includes a radio frequency switch or an electronic switch; the radio frequency switch is connected to the signal processing unit; the electronic switch is connected to the signal processing unit.

[0055] In other words, in the present invention, three sets of transmitting antennas and receiving antennas are arranged at different positions of the aircraft. The three sets of antennas respectively correspond to the positions directly below the aircraft when the roll angle of the aircraft is 0°, +60°, and -60°. Through the attitude sensing and control unit, the attitude of the aircraft is sensed. When the roll angle of the aircraft reaches the corresponding angle, the double-pole triple-throw switch is controlled to switch the transmitted signal and the received signal to the corresponding transmitting antenna and receiving antenna, so as to achieve the adaptation to the roll angle of the highly maneuverable aircraft.

[0056] Embodiment Example 1 Figure 4 shows a principle block diagram of a complete radio altimeter adapted to a highly maneuverable aircraft.

[0057] The functions of each module are as follows: The gyroscope is responsible for sensing the attitude of the aircraft. This signal can also be directly provided by the aircraft. After the signal processing unit receives the roll angle given by the gyroscope or the aircraft, according to the currently used antenna and the roll angle data, the transmitting antenna and the receiving antenna are synchronously switched through the antenna switching switch.

[0058] Specifically, the antenna switching switch uses a relay radio frequency switch or an electronic switch;

[0059] Specifically, the advantages and disadvantages of the electronic switch are as follows: First, it has a small volume and low power consumption, usually with a power consumption of the mw level; second, the switching speed is relatively fast, usually at the ns level; third, the insertion loss is relatively large, and the transmitted power needs to be increased for compensation; fourth, the isolation degree is small, and it is easily interfered by other antenna signals.

[0060] Specifically, the advantages and disadvantages of the mechanical switch are as follows:

[0061] First, it has a large volume and high power consumption, usually with a power consumption of the W level; second, the switching speed is slow, usually at the ms level; third, the insertion loss is small; fourth, the isolation degree is high, and it is not easily interfered by other antenna signals.

[0062] Specifically, in practical applications, the electronic or mechanical switch can be selected according to specific circumstances.

[0063] Specifically, the core classification and typical examples of the aircraft's maneuvers;

[0064] The maneuvers of the aircraft are tactical flight maneuvers realized through the flight control system, mainly divided into four categories: horizontal maneuver, vertical maneuver, compound maneuver, and post-stall maneuver. The purpose is to gain a position advantage or avoid attacks in air combat.

[0065] Specifically, the horizontal maneuver is an in-plane action, including sharp turn, roll maneuver, low-strongness turn, and barrel roll;

[0066] The sharp turn means that by pressing the control stick, the fuselage forms a 90-degree angle with the horizontal plane and quickly changes the heading, which is suitable for small-radius turning to avoid attacks;

[0067] The roll maneuver, that is, spiral rotation centered on the longitudinal axis of the fuselage, is often used to adjust the attitude or evade pursuit.

[0068] The low-strongness turn, that is, diving and accelerating with the nose lowered and then quickly turning, is used to pursue enemy aircraft fleeing at high speed.

[0069] The barrel roll (defensive / offensive), that is, changing the flight path through a spiral trajectory. The defensive barrel roll can lure enemy aircraft to charge forward, and the offensive barrel roll can avoid flying over enemy aircraft.

[0070] Specifically, the vertical maneuver is a three-dimensional space action, including: loop, Immelmann maneuver and Split-S;

[0071] The loop, that is, a loop, refers to pulling back the control stick to climb vertically to the inverted flight state and then recovering, completing a 180-degree heading reversal.

[0072] The Immelmann maneuver, that is, climbing vertically to the top and then performing a 180-degree roll, achieving a quick turn and occupying a height advantage.

[0073] The Split-S, that is, a separated S, refers to half-rolling and then diving, sacrificing height for speed and reversing the 180-degree heading, often used to break away from combat.

[0074] The compound maneuver is a multi-axis combined action, including: clockwise maneuver and Herbst pirouette;

[0075] The clockwise maneuver: climbing vertically to the apex and then quickly turning around the tail axis, resembling the rotation of the hands of a clock, used to quickly lock onto the target.

[0076] The J-Turn, Herbst pirouette, that is, combining a dive and a sharp turn, achieving a turn with an extremely small radius through vector thrust, enhancing the flexibility in close combat.

[0077] The post-stall maneuver is an unconventional action, including: Pugachev's cobra and Frolov's chakra;

[0078] The Pugachev's cobra, that is, suddenly decelerating at a large angle of attack to quickly raise the nose to over 110 degrees, forcing the trailing enemy aircraft to charge forward, applicable to the conversion between close-range offense and defense.

[0079] The Frolov's chakra, that is, following the cobra maneuver with a 360-degree flip, combining a loop with an extremely small radius in the stalled state, achieving multi-angle attacks.

[0080] The practical significance and system support of applying the present invention. Specifically, applying the energy maneuver theory, that is, by controlling the conversion of speed and height, namely kinetic energy and potential energy, to optimize the maneuver efficiency. For example, the cooperation between the low-strongness turn, acceleration and the high-strongness turn, recovery angle.

[0081] Vector thrust technology, such as fifth-generation fighter jets like the F-22 and the Su-57, enhances post-stall maneuverability through nozzle deflection.

[0082] Reference: The realization of maneuvering actions depends on the control of aerodynamic surfaces such as ailerons, rudders, and elevators, such as the coordinated movement of the control surfaces of the F-15E and the precise operation of the pilot on the throttle and joystick.

[0083] In the description of the present application, it should be understood that the orientation or positional relationship indicated by the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present application.

[0084] The specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Without conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. An altimeter antenna device adapted to the maneuvering actions of an aircraft, characterized in that, Comprising: An altimeter, an antenna switch, an attitude sensing and control unit, multiple sets of receiving antennas and transmitting antennas; The altimeter is installed on the surface of the aircraft; the outer ends of multiple sets of the receiving antennas and transmitting antennas are respectively installed on the surface of the aircraft at intervals according to a preset roll angle of the aircraft; the inner ends of multiple sets of the receiving antennas and transmitting antennas are connected and installed to the antenna switch in the altimeter; the attitude sensing and control unit is connected to the antenna switch; When the attitude of the aircraft changes, the attitude sensing and control unit can adjust the antenna switch to switch the receiving antennas and transmitting antennas corresponding to the current roll angle of the aircraft.

2. The altimetry antenna device adapted to the maneuvering actions of an aircraft according to claim 1, characterized in that, The angles of the preset roll angle of the aircraft are 0°, +60°, and -60° respectively.

3. The altimetry antenna device adapted to the maneuvering actions of the aircraft according to claim 2, wherein, The attitude sensing and control unit includes: a gyroscope and a signal processing unit; The signal processing unit can receive the roll angle of the gyroscope and then control the corresponding antenna switch according to the roll angle.

4. The altimetry antenna device adapted to the maneuvering actions of an aircraft according to claim 3, characterized in that, Comprising: Three sets of receiving antennas and transmitting antennas; The three sets of receiving antennas and transmitting antennas include: a first receiving antenna, a first transmitting antenna, a second receiving antenna, a second transmitting antenna, a third receiving antenna, and a third transmitting antenna; The outer ends of the first receiving antenna, the second receiving antenna, and the third receiving antenna are respectively installed on one side of the lower surface of the aircraft when the roll angle of the aircraft is 0°, +60°, and -60°; the outer ends of the first transmitting antenna, the second transmitting antenna, and the third transmitting antenna are respectively installed on the other side of the lower surface of the aircraft when the roll angle of the aircraft is 0°, +60°, and -60°; the inner ends of the first receiving antenna, the second receiving antenna, and the third receiving antenna are connected to the altimeter; the inner ends of the first transmitting antenna, the second transmitting antenna, and the third transmitting antenna are connected to the altimeter.

5. The altimetry antenna device adapted to the maneuvering actions of the aircraft according to claim 4, characterized in that, The antenna switch includes a radio frequency switch or an electronic switch; the radio frequency switch is connected to the signal processing unit; the electronic switch is connected to the signal processing unit.

6. The altimeter antenna device adapted to the maneuvering actions of an aircraft according to claim 3, characterized in that, The antenna switch is a double-pole triple-throw switch; the double-pole triple-throw switch can receive the signal from the signal processing unit and switch to the transmitting antenna and receiving antenna corresponding to the signal.

7. The altimetry antenna device adapted to the maneuver of the aircraft according to claim 6, characterized in that, The signal processing unit can receive the signal from the altimeter and output the current altitude information.

8. The altimetry antenna device adapted to the maneuvering of an aircraft according to claim 3, characterized in that, The gyroscope is installed inside the aircraft.

9. The altimetry antenna device adapted to the maneuver of the aircraft according to claim 6, characterized in that, Further comprising: A signal amplifier; the signal amplifier is connected to the signal processing unit; the signal amplifier is connected to the double-pole triple-throw switch.

10. The altimetry antenna device adapted to the maneuvering actions of the aircraft according to claim 6, characterized in that, The double-pole triple-throw switch can receive the signal from the receiving antenna and send it to the signal processing unit.

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