CN214690260U

CN214690260U - Electromagnetism towed aircraft mooring experiment platform

Info

Publication number: CN214690260U
Application number: CN202120676789.8U
Authority: CN
Inventors: 白顺科; 赵蕾; 崔群
Original assignee: Nanjing Vocational University of Industry Technology NUIT
Current assignee: Nanjing Vocational University of Industry Technology NUIT
Priority date: 2021-04-02
Filing date: 2021-04-02
Publication date: 2021-11-12
Anticipated expiration: 2031-04-02

Abstract

The utility model discloses an electromagnetism towed aircraft mooring experiment platform relates to the unmanned vehicles field. The utility model discloses a frame, locate the air grid module of being constituteed by air grid down in the frame, four side air grids and last air grid, locate the buffering bars above the lower air grid of air grid module, wear to locate the cable drum at the lower air grid middle part of air grid module, pass cable drum and the upper end mooring rope of mooring in the aircraft, controller and air-blower, the coil of a set of electromagnetism ring of establishing in the cable drum according to A/B/C three-phase alternate lead to with the alternating current and with inlay a set of iron core ring of locating in the mooring rope and take place the electromagnetic coupling and produce the mooring effort to connecting in the aircraft of mooring rope head end. The utility model has the advantages of small size, simple structure, capability of providing small mooring traction force, low cost, convenient use and the like.

Description

Electromagnetism towed aircraft mooring experiment platform

Technical Field

The utility model relates to an unmanned vehicles field, concretely relates to electromagnetism towed aircraft mooring experiment platform.

Background

In the research and manufacture of unmanned aerial vehicles, flight tests are usually required to be carried out on miniature aircrafts, and due to the fact that the miniature aircrafts have the characteristics of light weight, low lift force, low power and the like, if traditional large wind tunnel facilities are used for testing, the required test cost is inevitably high, and the high time and economic cost also make a plurality of small enterprises difficult to support. In addition, the power, especially the lift force, of some micro-aircraft is very small, even equivalent to the gravity of several grams, so that the problem of microliter force retention of such aircraft is also needed to be solved.

In summary, in the field of research and manufacture of unmanned aerial vehicles, a micro mooring experiment table which is small in size, simple in structure, capable of simulating aerodynamic force, capable of providing micro mooring resistance, low in cost and convenient to use is needed.

Disclosure of Invention

An object of the utility model is to provide an electromagnetism towed aircraft captive test platform to solve the above-mentioned defect that prior art exists.

The utility model provides an electromagnetism towed aircraft captive test platform, which comprises a frame, locate in the frame and by the air grid module that down air grid, four side air grids and last air grid constitute, locate the buffer grid of air grid module in down on the air grid, wear to locate the guy rope section of thick bamboo in the middle part of the air grid module in down the air grid, pass guy rope section of thick bamboo and the upper end is tethered in the mooring rope of aircraft, controller and air-blower, down air grid, side air grid and last air grid all are connected through trachea and electric connection to the air-blower of controller.

Preferably, the lower air grid, the side air grid and the upper air grid are in flat box-shaped structures, and air holes are formed in one surface facing the inner side of the lower air grid, the side air grid and the upper air grid.

Preferably, a buffer net made of porous braided fabric is arranged in the buffer grid in an expanded mode.

Preferably, the cable guide cylinder comprises a cable guide cylinder seat which is cylindrical in structure, the cross section of an upper opening and a lower opening of the cable guide cylinder seat is arc-shaped, a cable guide cylinder locking ring is connected with a group of at least 6 electromagnetic rings embedded in the cable guide cylinder seat through threads from the lower end of the cable guide cylinder seat, the coils of the electromagnetic ring group connected with the controller are alternately electrified with alternating current according to A/B/C three phases, and the frequency of the alternating current is 50-2000 Hz.

Preferably, the mooring rope comprises a rope sleeve made of rubber, a rope head embedded in the head end of the rope sleeve, a group of isolating rings and iron core rings which are arranged in the rope sleeve in a penetrating mode and distributed alternately, a rope tail hoop sleeved in the tail end of the rope sleeve, and a mooring ring which is arranged on the rope head and facilitates mooring of the aircraft, and the length of each pair of the isolating rings and the iron core rings which are distributed alternately in the rope sleeve is equal to the length of each electricity-saving magnetic ring in the rope guiding cylinder.

The utility model has the advantages that: the utility model discloses an electromagnetic ring group produces decurrent electromagnetic tension and produces the mooring effect to the aircraft to the iron core ring in the mooring cable according to A/B/C three-phase circular telegram in turn in the messenger's cable section of thick bamboo. When the lift force of the aircraft is increased or reduced, no matter the aircraft ascends or descends, the downward electromagnetic pulling force generated by the cable guide cylinder on the mooring cable is dynamically balanced with the gravity of the mooring cable and the gravity of the aircraft and the lift force of the aircraft, so that the mooring cable is always kept in a stretched mooring state, and the reliable mooring of the aircraft is guaranteed. The utility model has the advantages of small size, simple structure, capability of providing small mooring traction force, low cost, convenient use and the like.

Drawings

Fig. 1 is a schematic view of the overall configuration of an embodiment of the present invention.

Fig. 2 is a detailed view of the construction cross section of an embodiment of the invention.

Fig. 3 is a detailed view of a partial structure of an embodiment of the present invention.

Fig. 4 is a schematic view of an air supply and control system according to an embodiment of the present invention.

In the figure, a frame 1, a wind grid module 2, a buffer grid 3, a cable guide cylinder 4, a mooring cable 5, a controller 6 and a blower 7.

A lower air grid 21, a side air grid 22 and an upper air grid 23; a buffer net 31; a cable guide cylinder seat 41, an electromagnetic ring 42, a cable guide cylinder lock ring 43; a cable sleeve 51, a cable head 52, a spacer ring 53, a core ring 54, a cable tail hoop 55 and a tie ring 56; an aircraft 1000.

Detailed Description

In order to make the technical means, creation features, achievement purposes and functions of the present invention easy to understand, the present invention is further described below with reference to the following embodiments.

The embodiment of the utility model provides a refer to fig. 1-4, an electromagnetism towed aircraft captive test platform, including frame 1, locate frame 1 on and by air grid 21 down, four air grid module 2 that side air grid 22 and last air grid 23 are constituteed, locate the air grid module 2 in the buffer grid 3 of air grid 21 above, wear to locate air grid module 2 in the air grid guide 4 at air grid 21 middle part down, pass guide 4 and the upper end captive cable 5 of aircraft, controller 6 and air-blower 7, air grid 21 down, side air grid 22 and last air grid 23 all are connected through trachea and electric connection to controller 6's air-blower 7.

In the present embodiment, the lower air grid 21, the side air grid 22 and the upper air grid 23 are each of a flat box-shaped structure, and air holes are formed on one surface facing the inside.

In this embodiment, a buffer net 31 made of a porous woven fabric is stretched inside the buffer grid 3.

In the embodiment, the cable guide cylinder 4 comprises a cable guide cylinder seat 41 which is cylindrical in structure and has an arc-shaped cross section of the upper opening and the lower opening, a cable guide cylinder lock ring 43 is embedded in the cable guide cylinder seat by screwing a group of electromagnetic rings 42 with the number not less than 6 from the lower end of the cable guide cylinder seat 41, the coils of the group of electromagnetic rings 42 connected with the controller 6 are alternately electrified with alternating current according to A/B/C three phases, and the frequency of the alternating current is 50-2000 Hz.

In this embodiment, the mooring rope 5 includes a rope sleeve 51 made of rubber, a rope head 52 embedded in the head end of the rope sleeve 51, a set of isolating rings 53 and iron core rings 54 alternately arranged in the rope sleeve 51, a rope tail hoop 55 sleeved on the tail end of the rope sleeve 51, and a mooring ring 56 arranged on the rope head 52 for mooring the aircraft, and the length of each pair of isolating rings 53 and iron core rings 54 alternately arranged in the rope sleeve 51 is equal to the length of each electricity-saving magnetic ring 42 in the rope guide cylinder 4.

In this embodiment, the frame 1, the frames of the air grids, and the frames of the buffer grids are made of metal profiles, the buffer net 31 is made of a porous braided fabric, the panels on the air grids are made of metal, plastic, or transparent organic glass, the rope guide cylinder seat 41 and the rope guide cylinder locking ring 43 of the rope guide cylinder 4 are made of plastic, and the electromagnetic ring 42 of the rope guide cylinder 4 is made of an existing annular electromagnet standard part or a fixed part. The cable sleeve 51 of the mooring cable 5 is made of rubber materials, the cable head 52 and the isolating ring 53, the iron core ring 54 is made of ferromagnetic materials, the cable hoop 55 is an annular spring hoop or a rubber ring, and the mooring ring 56 is made of soft braided ropes. The controller 6 is customized by universal parts, and the blower 7 is customized by universal parts.

The working process of the embodiment is as follows:

referring to fig. 1-4, when the present embodiment is used in an aircraft mooring experiment, it is only necessary to place the aircraft 1000 on the bumper fence 3, and to moor one end of the mooring rope 5 to the aircraft 1000, and the other end of the mooring rope 5 is inserted into the rope guiding cylinder seat of the rope guiding cylinder 4 and suspended below the frame 1. When the aircraft is subjected to mooring experiments, the controller 6 can control the speed of air flow blown into the inner side or drawn out of each air grid of the air grid module 2 from the inner side so as to form specific air flow around the aircraft to test the flight state of the aircraft, and meanwhile, the electromagnetic rings 42 in the cable guide cylinder 4 are alternately electrified according to the A/B/C three phases to generate downward electromagnetic tension on the iron core ring 54 in the mooring cable 5 so as to generate mooring effects on the aircraft. When the lift force of the aircraft is increased or reduced, no matter the aircraft ascends or descends, the downward electromagnetic pulling force generated by the cable guide cylinder 4 on the mooring cable 5 is dynamically balanced with the gravity of the mooring cable 5 and the gravity of the aircraft and the lift force of the aircraft, so that the mooring cable 5 is always kept in a stretched mooring state, and the reliable mooring of the aircraft is ensured.

It will be appreciated by those skilled in the art that the invention may be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The embodiments disclosed above are therefore to be considered in all respects as illustrative and not restrictive. All changes which come within the scope of the invention or which are equivalent to the scope of the invention are embraced by the invention.

Claims

1. The utility model provides an electromagnetism towed aircraft captive test platform which characterized in that: including frame (1), locate on frame (1) and by wind grid module (2) that down wind grid (21), four side wind grids (22) and last wind grid (23) are constituteed, locate in wind grid module (2) buffer grid (3) above wind grid (21) down, wear to locate wind grid module (2) in the wind cable guide tube (4) of wind grid (21) middle part down, pass cable guide tube (4) and upper end mooring in aircraft mooring rope (5), controller (6) and air-blower (7), down wind grid (21), side wind grid (22) and last wind grid (23) all are connected with air-blower (7) of electric connection to controller (6) through the trachea.

2. The electromagnetic towed aircraft mooring test bed of claim 1, wherein: the lower air grid (21), the side air grids (22) and the upper air grid (23) are all in a flat box-shaped structure, and air holes are formed in one surface facing the inner side.

3. The electromagnetic towed aircraft mooring test bed of claim 1, wherein: a buffer net (31) made of porous braided fabric is arranged in the buffer grid (3) in an opening mode.

4. The electromagnetic towed aircraft mooring test bed of claim 1, wherein: the cable guide cylinder (4) comprises a cable guide cylinder seat (41) which is cylindrical in structure, the cross section of an upper opening and a lower opening of the cable guide cylinder seat is arc-shaped, a cable guide cylinder lock ring (43) is connected with a group of at least 6 electromagnetic rings (42) from the lower end of the cable guide cylinder seat (41) through threads, the group of electromagnetic rings (42) is embedded into the cable guide cylinder seat, the coils of the group of electromagnetic rings (42) connected with the controller (6) are alternately electrified with alternating current according to A/B/C three phases, and the frequency of the alternating current is 50-2000 Hz.

5. The electromagnetic towed aircraft mooring test bed of claim 1, wherein: the mooring rope (5) comprises a rope sleeve (51) made of rubber, a rope head (52) embedded at the head end of the rope sleeve (51), a group of isolating rings (53) and iron core rings (54) which are arranged in the rope sleeve (51) in a penetrating mode and distributed alternately, a rope tail hoop (55) sleeved at the tail end of the rope sleeve (51), and a mooring ring (56) arranged on the rope head (52) and convenient for mooring an aircraft, wherein the length of each pair of the isolating rings (53) and the iron core rings (54) distributed in the rope sleeve (51) alternately is equal to the length of each electricity-saving magnetic ring (42) in the rope guide cylinder (4).