CN106403718B - A kind of recoverable electric power rocket for intercepting small aircraft - Google Patents

Abstract

The invention discloses a recoverable electric powered rocket for intercepting small aircraft, which comprises a fairing, a distance sensor, a release valve, an air inlet, a motor bracket, a secondary propeller, a primary thrust motor, a primary propeller, a tail Rudders, landing sensors, tail rudder motors, secondary thrust motors, rocket shells, connecting ribs, electrical control cabins, high-pressure gas chambers, parachutes, image recognition devices, catch nets and fairing connecting wires. The recyclable electric rocket of the present invention does not rely on fuel to work, is safe to use, can automatically find, track and capture targets, has strong applicability, can be recycled and reused, and has low use cost.

Description

A retrievable electro-powered rocket for intercepting small aircraft

technical field

The invention relates to the field of aircraft, in particular to a recoverable electric rocket for intercepting small aircraft.

Background technique

With the continuous maturity of remote sensing technology, navigation technology and electronic technology, the production cost of small unmanned aerial vehicles has gradually decreased, and its application scope and scale have expanded rapidly. Small unmanned aerial vehicles have brought convenience to industry, agricultural production or other fields, but they have also brought certain hidden dangers to public safety. Relevant departments have set up no-fly zones for small unmanned aerial vehicles and gradually introduced relevant management measures. However, there are always incidents of aircraft out of control or malicious intrusion, and small unmanned aerial vehicles need to be captured or intercepted. Due to their small size, low cost, and flexible flight routes, low-altitude small unmanned aerial vehicles are not suitable for general military ground-to-air interception devices, especially in densely populated areas. There are several types of existing small aircraft interception devices, such as ground-launched capture nets, drone-carried capture nets, and electronic jamming, which generally have problems such as short effective distance, slow capture speed, low reliability, and high cost of use.

Contents of the invention

The purpose of the present invention is to overcome the disadvantages in the prior art, and provide a retrievable electric rocket for intercepting small aircrafts with high capture speed, high reliability and low cost.

The object of the present invention is achieved through the following technical solutions:

A retrievable electric powered rocket for intercepting small aircraft, including a fairing 1, a distance sensor 2, a release valve 3, an air inlet 4, a motor bracket 5, a secondary propeller 6, a primary thrust motor 7, a primary Propeller 8, tail rudder 9, landing sensor 10, tail rudder motor 11, secondary thrust motor 12, rocket shell 13, connecting rib 14, electrical control cabin 15, high-pressure air chamber 16, parachute 17, image recognition device 18, capture Netting 19 and fairing connecting wire 20.

The external structure of the recoverable electric power rocket is: the top of the cylindrical rocket case 13 is plugged with a fairing 1, and the fairing 1 and the rocket case 13 are connected by a fairing connection line 20; A distance sensor 2 and an image recognizer 18 are symmetrically installed on the outer side of the upper part, and four tail rudders 9 are installed symmetrically on the outer side of the lower part of the rocket shell 13, and each tail rudder 9 is controlled by a tail rudder motor 11, and the tail rudder motor 11 Electrical energy and control signals are provided by the electrical control cabin 15; a landing sensor 10 is installed at the tail of the rocket shell 13.

The internal structure of the recyclable electric power rocket is: the middle part of the rocket shell 13 is provided with four air inlets 4, and the rocket shell 13 is divided into upper and lower parts, which are fixedly connected with four connecting ribs 14 in the middle; The upper space of 4 is the electrical control cabin 15, which is sealed and connected with the rocket casing 13, and lithium-ion batteries and control circuits are placed inside to provide electric energy and electrical control for the entire rocket; above the electrical control cabin 15 is a high-pressure gas The warehouse 16 stores high-pressure gas in the initial state and is used to spray the parachute 17 and the catch net 19; the top of the high-pressure gas warehouse 16 is equipped with a release valve 3, which is opened by the control of the electric control cabin 15, and is used to quickly release the compressed gas to generate thrust; The space above the high-pressure gas chamber 16 is placed with a parachute 17. The parachute 17 is in a compressed state when it is inside the rocket, and it is in an open state after spraying. Its rope is connected with the rocket shell 13; The inside of the rocket is in a compressed state, and after being ejected, it is in an open state and breaks away from the rocket shell 13 .

There are two cross-shaped motor brackets 5 in the space below the air inlet 4, and the two motor brackets 5 are arranged in series, and their edges are fixedly connected with the rocket shell 13, and a first-stage thrust motor 7 and a second-stage thrust motor 12 are respectively fixed at the middle positions The first-stage thrust motor 7 is below, and the second-stage thrust motor 12 is above, and the first-stage propeller 8 and the second-stage propeller 6 are installed correspondingly respectively; Signal. The interior of the space below the air inlet 4 is transparent, providing a channel for the high-speed flow of air; the air enters from the air inlet 4, is pushed by the two-stage propeller, and is discharged at high speed from directly below the rocket shell 13 to generate thrust, which is an electric power rocket. Provides flight power.

Compared with the prior art, the present invention has the following advantages and effects:

(1) The recoverable electric power rocket of the present invention does not rely on fuel to work and is safe to use.

(2) The recoverable electric powered rocket of the present invention can automatically find, track and capture targets, and has strong applicability.

(3) The recoverable electric power rocket of the present invention can be recovered and reused, and has low use cost.

Description of drawings

Fig. 1 is a schematic diagram of the longitudinal section structure of the recoverable electric powered rocket of the present invention.

Fig. 2 is a working schematic diagram of the ejection catch net of the retrievable electric rocket of the present invention.

Fig. 3 is a schematic diagram of opening the parachute of the retrievable electric powered rocket of the present invention.

Fig. 4 is a schematic cross-sectional view of the air inlet.

Fig. 5 is a schematic cross-sectional view of the motor bracket.

Figure 6 is a schematic cross-sectional view of the tail rudder.

Among them, 1. fairing; 2. distance sensor; 3. release valve; 4. air inlet; 5. motor bracket; 6. secondary propeller; 7. primary thrust motor; 8. primary propeller; Rudder; 10, landing sensor; 11, tail rudder motor; 12, two-stage thrust motor; 13, rocket shell; 14, connecting rib; 15, electrical control cabin; 16, high-pressure air chamber; 17, parachute; 18, image Identifier; 19, catch net; 20, fairing connecting line.

Detailed ways

The present invention will be described in further detail below in conjunction with the examples, but the embodiments of the present invention are not limited thereto.

Example 1

A retrievable electro-powered rocket for intercepting small aircraft, as shown in Figure 1, includes a fairing 1, a distance sensor 2, a release valve 3, an air inlet 4, a motor bracket 5, a secondary propeller 6, a primary Thrust motor 7, primary propeller 8, tail rudder 9, landing sensor 10, tail rudder motor 11, secondary thrust motor 12, rocket shell 13, connecting rib 14, electrical control cabin 15, high-pressure gas chamber 16, parachute 17, Image recognizer 18, catch net 19 and fairing cover connecting line 20.

The external structure of the recoverable electric power rocket is: the top of the cylindrical rocket case 13 is plugged with a fairing 1, and the fairing 1 and the rocket case 13 are connected by a fairing connection line 20; A distance sensor 2 and an image recognizer 18 are symmetrically installed on the outer side of the upper part, and four tail rudders 9 are installed symmetrically on the outer side of the lower part of the rocket shell 13, and each tail rudder 9 is controlled by a tail rudder motor 11. As shown in FIG. 6 , the tail rudder motor 11 is provided with electric energy and control signals by the electrical control cabin 15 ; a landing sensor 10 is installed at the tail of the rocket shell 13 .

The internal structure of the recyclable electric power rocket is: the middle part of the rocket shell 13 is provided with four air inlets 4, the rocket shell 13 is divided into upper and lower parts, and the middle part is fixedly connected with four connecting ribs 14, as shown in Figure 4 As shown; the space above the air inlet 4 is an electrical control cabin 15, which is sealed and connected with the rocket shell 13, and a lithium-ion battery and a control circuit are placed inside to provide electric energy and electrical control for the entire rocket; the electrical control cabin Above 15 is a high-pressure gas chamber 16, which stores high-pressure gas in the initial state and is used to spray parachutes 17 and catch nets 19; a release valve 3 is installed on the top of the high-pressure gas chamber 16, which is opened by the electrical control cabin 15 for quick release Compress the gas to generate thrust; the upper space of the high-pressure gas chamber 16 is placed with a parachute 17, which is in a compressed state when inside the rocket, and is in an open state after being sprayed, and its rope is connected with the rocket shell 13; the top of the parachute 17 is a catch net 19. The catch net 19 is in a compressed state when inside the rocket, and is in an open state after being sprayed, and is separated from the rocket shell 13.

There are two cross-shaped motor brackets 5 in the space below the air inlet 4, as shown in Figure 5, the two motor brackets 5 are arranged in series, their edges are fixedly connected to the rocket shell 13, and a first-stage thrust motor 7 is respectively fixed at the middle position and two-stage thrust motor 12; one-stage thrust motor 7 is below, and two-stage thrust motor 12 is above, and one-stage propeller 8 and two-stage propeller 6 are correspondingly installed respectively; one-stage thrust motor 7 and two-stage thrust motor 12 are electrically controlled Module 15 provides electrical power and control signals. The interior of the space below the air inlet 4 is transparent, providing a channel for the high-speed flow of air; the air enters from the air inlet 4, is pushed by the two-stage propeller, and is discharged at high speed from directly below the rocket shell 13 to generate thrust, which is an electric power rocket. Provides flight power.

When the rocket is in the initial state, the high-pressure gas chamber 16 stores compressed gas, the release valve 3 is in a closed state, the catch net 19 and the parachute 17 are compressed in the rocket shell 13, and the fairing 1 is plugged on the rocket shell 13.

When the captured target (such as a small aircraft) enters the captured airspace, use auxiliary facilities or manually point the head of the rocket towards the captured target, the remote control signal will start the rocket, and the rocket will fly autonomously after it lifts off; when the rocket is flying, the image recognizer 18 Obtain image information in front of the rocket, transmit it to the electrical control cabin 15 to identify the position of the captured target, and transmit the rocket flight trajectory control signal to the tail rudder motor 11; when the rocket is close to the captured target, the effective distance is sensed by the distance sensor 2 and transmitted The signal is given to the electrical control cabin 15, and the electrical control cabin 15 triggers the release valve 3, and the compressed high-pressure gas in the high-pressure gas chamber 16 ejects the parachute 17 and the catch net 19 out of the rocket shell 13, and the fairing 1 is opened, as shown in Figure 2; After the net 19 breaks away from the rocket casing 13, it is free to open by inertia until it touches the captured target; after the release valve 3 is triggered, the two thrust motors stop working, the rocket falls under the action of gravity, and the parachute 17 opens, and the rocket is released. The falling speed is constrained within a certain range, as shown in Figure 3; when the rocket lands to a certain distance from the ground, the landing sensor 10 installed at the tail of the rocket casing 13 is triggered, and the electrical control cabin 15 starts the first-stage thrust motor 7 to rotate at a low speed , the reverse thrust generated further reduces the landing speed of the rocket and ensures that the rocket is in safe contact with the ground. Rocket recovered.

Claims (2)

1. A retrievable electric powered rocket for intercepting small aircraft, characterized in that: comprising a fairing, a distance sensor, a release valve, an air inlet, a motor support, a secondary propeller, a primary thrust motor, and a primary propeller , tail rudder, landing sensor, tail rudder motor, two-stage thrust motor, rocket shell, connecting ribs, electrical control cabin, high-pressure air tank, parachute, image recognition device, catch net and fairing connection line; recyclable electric power The external structure of the rocket is: the top of the cylindrical rocket shell is plugged with a fairing, and the fairing and the rocket shell are connected by a fairing connection line; the upper outer side of the rocket shell is symmetrically installed with distance sensors and image recognition. Four tail rudders are symmetrically distributed on the outer side of the lower part of the rocket shell, each tail rudder is controlled by a tail rudder motor, and the tail rudder motor is provided with electric energy and control signals by the electrical control cabin; Landing sensor; the internal structure of the recoverable electric rocket is: there are four air inlets in the middle of the rocket shell, which divides the rocket shell into upper and lower parts, and the middle part is fixed and connected with four connecting ribs; The upper space is the electrical control cabin, which is sealed and connected to the rocket shell. Lithium-ion batteries and control circuits are placed inside to provide electric energy and electrical control for the entire rocket; the upper part of the electrical control cabin is a high-pressure gas chamber. Store high-pressure gas for spraying parachutes and catch nets; a release valve is installed on the top of the high-pressure gas chamber, which is opened by the electrical control cabin for rapid release of compressed gas to generate thrust; a parachute is placed in the space above the high-pressure gas chamber. It is in a compressed state when inside the rocket, and it is in an open state after spraying, and its rope is connected to the rocket shell; above the parachute is a catch net, which is in a compressed state when inside the rocket, and it is in an open state after spraying, and is separated from the rocket shell . 2. The recyclable electric powered rocket for intercepting small aircraft according to claim 1, characterized in that: there are two cross-shaped motor supports in the space below the air inlet, and the two motor supports are arranged in series, and the edges of the two motor supports are arranged in series with the The rocket shell is fixedly connected, and the middle position is fixed with a primary thrust motor and a secondary thrust motor; and the two-stage thrust motor are provided with electric energy and control signals by the electrical control cabin.