JPS6217117Y2 - - Google Patents

Description

[Detailed Description of the Invention] The present invention relates to a stall detection mechanism in a radio-controlled vehicle.
It also relates to a mechanism that sounds a stall warning alarm if the speed drops below a certain level.

With radio control, a receiver mounted on the model receives radio waves emitted from a transmitter on the control side, and a servo motor operates according to instructions from the transmitter to control the flying direction, speed, etc. of the model. be. Radio-controlled models include airplanes, cars, ships, etc., but airplanes flying in the air require a minimum speed to maintain a balance between buoyancy and their own weight, and are also capable of achieving the highest speed. . The control range of radio controls is usually about 1 km, so the airplane must always be located within a radius of 1 km, and depending on the model, the stall speed is approximately fixed, and if the speed is lower than that, it will crash. It turns out. There is a method for the pilot to detect the flight speed of the airplane as a way to prevent the model airplane from going out of control and going into a so-called non-contact state, or from stalling and crashing, and the inventor has already filed a patent application for this method. did. However, in order to actually fly a radio-controlled airplane, it is necessary to keep the airplane in sight at all times, and checking the speedometer numbers requires considerable skill. Therefore, the inventor further thought of a mechanism that would generate an alarm when an airplane reaches a certain speed, and came up with the present invention.

Therefore, an object of the present invention is to provide a mechanism in which the speed of a radio-controlled flying object is detected by the operator, and an alarm is generated when the speed reaches a predetermined value.

That is, the present invention has a propeller protruding forward from the main body of the model aircraft so that it can freely rotate, is equipped with a transmitter that converts the rotation of the propeller into a pulse signal, and transmits the pulse signal. A circuit that converts the sent pulse signal into rotational speed to display the speed of the flying object, and a comparison circuit consisting of a multivibrator converts the pulse signal into an intermittent electronic switch to display the speed of the flying object. This is a stall detection mechanism for a flying object in a radio-controlled vehicle, which is provided with a separate receiver having a stall detection circuit that generates an alarm in response.

The present invention will be explained in detail below with reference to the drawings. FIG. 1 is a perspective view of a model airplane in which the speed-detecting propeller of the present invention is attached to the fuselage. In Fig. 1, a model airplane 1 has built-in engines, receivers, servo motors, batteries, etc. (all not shown) that would normally be installed, and a propeller for speed detection in the front part of the right wing 2. 3 is attached to protrude forward from the main body and freely rotate,
A sensor (hereinafter referred to as CDS) 4 is provided behind the propeller 3 to detect interruptions in light due to rotation of the propeller. Also, there is a CDS on board.
There is a built-in transmitter (not shown) that converts the number of propeller revolutions output from 4 into a pulse signal and transmits it.

FIG. 2 is an enlarged side sectional view of the speed detection propeller section, FIG. 3 is a view taken along the line B-B in FIG. 2, and FIG. 4 is a view taken along the line A-A in FIG. 2 to 4, a propeller mounting base 5 is screwed to the front part of the right wing 2 of a model airplane with bolts 6 and nuts 4. The propeller mounting base 5 has a screw 8 carved into the tip of the cylinder, and a cylinder 8' with a smaller diameter protrudes from the tip, and wing-shaped plates 5' extend horizontally on both sides of the large diameter cylinder. The central part of this board can be screwed in with a bolt. A stay 9 is screwed onto the screw 8 of the propeller mounting base 5. The stay 9 is composed of a cylindrical propeller bearing rod 10, a CDS receptor 11 located below the propeller bearing rod 10, and a support plate 12 that supports these.
A speed detection propeller 3 is attached via 3 so as to be freely rotatable. In addition, CDS receptor 11
The CDS 4 is housed with the sensing section 14 facing the propeller, and the cord 15 passes through the right wing 2 and is connected to a transmitter (not shown) inside the aircraft.

FIG. 5 is a circuit diagram of the transmitter, which is composed of a pulse conversion circuit 16 that converts the intermittent light (rotation speed) sent from the CDS 4 into a pulse signal and a transmitter circuit 17 that transmits this pulse signal.

FIG. 6 is a circuit diagram of the receiver, and the antenna 18
A radio wave receiving circuit 19 detects and extracts a pulse signal by receiving radio waves from the air, a speed display circuit 20 converts the pulse signal into a rotational speed and displays the flight speed on a speedometer, and a multivibrator converts the pulse signal by a circuit 21, 21. It is comprised of a stall detection circuit 24 and a power supply circuit 25, which convert the electronic switch 22 to intermittent mode via a comparison circuit, and generate an alarm from the earphone or speaker 23 when the speed drops below a certain level.

The operating status of the present invention will be explained below.

A model airplane flying by a known method experiences air resistance at the speed detection propeller 3, so this propeller rotates at a rotational speed corresponding to the flight speed.
On the other hand, the CDS 4 has a sensing section 14 immediately after the propeller 3.
Since the sensor is installed facing the propeller, the intermittent light that changes each time the propeller passes in front of the sensing unit 14 is accurately sensed and counted as the number of revolutions of the propeller. The signal output from the CDS 4 is converted into a pulse signal by a pulse conversion circuit 16 on the transmitter side, and further transmitted to the ground via a transmission circuit 17.
This signal is caught by the antenna 18 of the receiver owned by the pilot on the ground, and the pulse signal taken out by the radio wave receiving circuit 19 is branched and a part of it is input to the speed display circuit, where the pulse signal is is converted into a rotational speed, and the flight speed of the aircraft is displayed on a speedometer whose scale has been calibrated in advance based on the relationship between the measured rotational speed and speed. On the other hand, the pulse signal output from the radio wave receiving circuit 19 is simultaneously branched into the stall detection circuit 24 and triggers the multivibrator circuit 21 (the circuit shown on the left side in FIG. 6). Then, the output and resistance value from the same circuit 21 to the multivibrator circuit shown on the right side in Fig. 6 (figure number 2 in Fig. 6)
The multivibrator circuit 21 ( The electronic switch 22 repeatedly turns on and off due to changes in the voltage output from the multivibrator circuit (shown on the right side in FIG. 6), and an alarm is generated from the earphone or speaker 23. Therefore, the operator can hear this alarm and immediately increase the speed and adjust it to the desired speed.

In the present invention, the transmitter mounted on the aircraft and the receiver on the ground are normally configured separately from the receiver mounted on the aircraft for maneuvering and the transmitter on the ground. It is also possible to integrate it as a single unit. Further, the propeller mounting position for speed detection is not particularly limited and may be mounted at a location other than the blade. It also detects intermittent light as a speed detection mechanism.
Although the example of CDS has been described, other methods of obtaining changes in voltage strength using magnets, optical elements, etc. are also possible, and any of these methods can be used in the present invention. In addition, although we have given an example in which the stall warning alarm occurs when the speed drops below a certain level, there are other methods such as a method in which the alarm is generated only when a certain speed is reached, or a method in which the alarm is stopped only when a specific speed is reached. It can also be adopted. The alarm can also be heard by the pilot using earphones, or the sound can be amplified using speakers. Furthermore, it is of course possible to turn on or flash a warning lamp.
All of these are included within the technical scope of the present invention.

The present invention as described above has the following effects.

(1) When a model aircraft in flight becomes slower than a preset speed, an alarm is generated and the operator can sense this, allowing the operator to immediately adjust the speed and prevent crashes due to stalling. .

(2) If you set up a mechanism in advance that generates an alarm only at a predetermined speed, this will serve as a guideline for controlling the attitude during takeoff and landing, making maneuvering extremely reliable.

(3) Specific speed range, e.g. 50-150Km/
By creating a mechanism that does not generate an alarm only in the hr range, it is possible to maintain a flight condition at an appropriate speed at all times.

(4) Also, the flight speed is finally displayed on the speedometer, allowing for accurate maneuvering.

[Brief explanation of the drawing]

Fig. 1 is a perspective view of the model airplane, Fig. 2 is an enlarged side sectional view of the speed detection propeller section, Fig. 3 is a view taken along the line B-B in Fig. 2, and Fig. 4 is a view taken along the line A-A in Fig. 2. 5 is a circuit diagram of the transmitter, and FIG. 6 is a circuit diagram of the receiver. 1...Model airplane, 2...Right wing, 3...Speed detection propeller, 4...CDS, 5...Propeller mounting base, 5'...Plate, 6...Bolt, 7...Nut, 8... Screw, 8'...Cylinder, 9...Stay,
10... Propeller bearing rod, 11... CDS receptor, 12... Support plate, 13... Propeller shaft, 14
...Sensing section, 15 ... Code, 16 ... Pulse conversion circuit, 17 ... Transmission circuit, 18 ... Antenna,
19...Radio wave receiving circuit, 20...Speed display circuit, 21...Multi-vibrator circuit, 22...
...electronic switch, 23... earphone or speaker, 24... stall detection circuit, 25... power supply circuit.

Claims (1)

[Scope of utility model registration request] A propeller is attached to the model flying vehicle so that it can freely rotate by protruding forward from the main body, and a transmitter that converts the rotation of the propeller into a pulse signal and transmits it is installed, and a pulse signal is sent from the transmitter. A circuit that converts the number of rotations into the speed of the flying object to display the speed of the flying object, and a comparison circuit consisting of a multivibrator converts the pulse signal into an intermittent electronic switch to generate an alarm according to the speed of the flying object. A stall detection mechanism for a flying object in a radio-controlled aircraft, comprising a separate receiver having a stall detection circuit.