CN214029165U - Aircraft system based on missile power propulsion - Google Patents

Abstract

The utility model discloses an aircraft system based on guided missile power propulsion, guided missile power propulsion aircraft comprises fuselage, wing and the inside aircraft flight control system of fuselage, guided missile driving system, guided missile flight control system and switch. The wings are arranged on two sides of the fuselage, and the missile is arranged on the wings or the fuselage; the missile mounting mode is that the fixed wing unmanned aerial vehicle carries the work, and the missile passes through stores pylon and connector direct mount on the wing. The missile mounting mode is multi-rotor unmanned aerial vehicle mounting work, and the missile is installed on the multi-rotor through a hanger and a connector. The utility model discloses a multiplexing of the thrust of guided missile helps the aircraft to realize the power backup, and when aircraft main engine trouble, help the aircraft breaks away from dangerous stall state, realizes the multiplexing thought of guided missile power.

Description

Aircraft system based on missile power propulsion

Technical Field

The utility model relates to a guided missile impels technical field, in particular to aircraft system based on guided missile power propulsion.

Background

The plane with striking ability is hung with a missile on the wing or the belly, and the missile is generally powered. At present, however, the power of the missile is generally started only when the missile is launched, and the power is not helpful for the takeoff and the flight of an airplane. For an aircraft, the missile influences the aerodynamic drag, and both the endurance and the speed increase of the aircraft are negatively influenced. In addition, the aircraft taking off by using the rocket boosting technology is utilized, the rocket engine is bound on the aircraft body of the aircraft, the rocket engine is started simultaneously when the aircraft takes off, and under the boosting of the rocket engine, the aircraft can accelerate at the fastest speed, so that the takeoff and running distance is shortened. However, these booster rockets are all special rockets and are discarded after the takeoff is finished. The technology of boosting the flight of an airplane by adopting the power on a missile has not been applied.

SUMMERY OF THE UTILITY MODEL

Based on the technical problem that the background art exists, the utility model provides a based on propulsive aircraft system of guided missile power, through the multiplexing of the thrust of guided missile, help the aircraft to realize shorter take off and land distance. On one hand, the airplane is helped to realize power backup through the reuse of the thrust of the missile, and when the main engine of the airplane breaks down, the airplane is helped to be separated from a dangerous stall state; and on the other hand, the aircraft flight control system is used for connecting and controlling a missile power system, so that the missile power multiplexing idea is realized.

The utility model is realized in such a way, the missile power propulsion-based airplane system comprises a body, wings, an airplane flight control system inside the body, a missile power system, a missile flight control system and a switcher; the wings are arranged on two sides of the fuselage, and the missile is arranged on the wings or the fuselage; the missile is fixed on the wing and the multiple rotors in a mounting working mode.

Furthermore, the missile mounting work mode has two kinds, one mode is fixed wing unmanned aerial vehicle mounting work, and the missile passes through the stores pylon and the connector direct mount on the wing. Another mounting working mode of the missile is multi-rotor unmanned aerial vehicle mounting work, and the missile is installed on the multi-rotor through a hanger and a connector.

Further, the switch is connected with the aircraft flight control system through a switching network and an aircraft flight control power control network.

Furthermore, the switcher is respectively connected with an airplane flight power control network of an airplane flight control system and a missile flight power control network of a missile flight control system, and the switcher is connected with the missile power system through a missile power network; the switch selects the network-connected missile power system according to a switching network given by the airplane flight control system.

Furthermore, an airplane flight force control network of the airplane flight control system is connected with a missile power system, and when the airplane flight force control network of the airplane flight control system is connected to the missile power system, the whole system works in a missile power propulsion state; the aircraft flight control system controls the power of the missile.

Furthermore, the missile flight control system is connected with a missile power system through a switcher on one hand, and the missile flight control system is connected into the missile power system through a missile flight power control network on the other hand.

Further, the switch controls network connection of the switching network, the airplane flight power control network, the missile power network and the missile flight power control network.

Compared with the prior art, the utility model following beneficial effect has.

1. The utility model discloses the fuselage is inside to be constituteed by aircraft flight control system, guided missile driving system, guided missile flight control system and switch, through the multiplexing of the thrust of guided missile, helps the aircraft to realize shorter take off and land distance. On one hand, the airplane is helped to realize power backup through the reuse of the thrust of the missile, and when the main engine of the airplane breaks down, the airplane is helped to be separated from a dangerous stall state; and on the other hand, the aircraft flight control system is used for connecting and controlling a missile power system, so that the missile power multiplexing idea is realized.

2. The utility model increases the power reserve and redundancy of the whole aircraft on the premise of not increasing the weight and cost of the system; the take-off and landing distance of the fixed-wing aircraft is shortened, and the emergency handling capacity of the aircraft is improved. To rotor aircraft, the utility model discloses can help it to realize bigger flat flying speed, help it to realize longer system idle time. The method has small influence on the original missile system, low implementation cost, small influence on the structure of the airplane and low implementation cost.

Drawings

Fig. 1 is a schematic structural diagram of an aircraft system based on missile power propulsion according to the present invention;

FIG. 2 is a schematic view of missile installation of an aircraft system based on missile power propulsion according to the present invention;

FIG. 3 is a schematic view of the mounting work of a fixed-wing UAV (unmanned aerial vehicle) of an aircraft system based on missile power propulsion provided by the utility model;

fig. 4 is the utility model provides a many rotor unmanned aerial vehicle of aircraft system carry work schematic diagram based on guided missile power propulsion.

Wherein: 100. fuselage, 101, wing, 101-1, multi-rotor, 102, missile, 103, pylon, 104, connector, 110, aircraft flight control system, 111, flight power control network, 112, switching network, 120, missile power system, 121, missile power network, 130, missile flight control system, 131, missile flight power control network, 140, switch.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

Referring to fig. 1, 2, 3 and 4, the present invention provides a missile power propulsion-based aircraft system, which is composed of a fuselage 100, wings 101, an aircraft flight control system 110 inside the fuselage 100, a missile power system 120, a missile flight control system 130 and a switch 140; the wings 101 are arranged on two sides of the fuselage 100, and the missiles 102 are arranged on the wings 101 or the fuselage 100; the missile 102 is fixed on the wing 101 and the multi-rotor 101-1 in a mounting working mode.

Referring to fig. 3, the missile 102 is mounted in two modes, one mode is fixed-wing drone mounting, and the missile 102 is directly mounted on the wing 101 through a hanger 103 and a connector 104.

Referring to fig. 4, another mounting operation mode of the missile 102 is that of a multi-rotor unmanned aerial vehicle, and the missile 102 is mounted on a multi-rotor 101-1 through a pylon 103 and a connector 104. The aircraft flight control system 110, the missile power system 120, the missile flight control system 130 and the switch 140 are cooperative with each other, and the switch 140 is used for controlling network input and output of the switching network 112, the aircraft flight power control network 111, the missile power network 121 and the missile flight power control network 131, so that independent work and mutual interference among the networks are realized. The aircraft flight control system 110 is a combination of flight automatic control subsystems with various functions on the aircraft, and can be used for ensuring the stability and maneuverability of the aircraft, improving the task completion capability and flight quality, enhancing the flight safety and lightening the burden of a driver; under various interference conditions, the missile power system 120 and the missile flight control system 130 stabilize the attitude of the missile 102, ensure that the deviation of the flight attitude angle of the missile 102 is within an allowable range, control the attitude angle of the missile according to a guidance instruction, adjust the flight direction of the missile 102, correct the flight path and enable the missile 102 to accurately hit a target.

The switch 140 is coupled to the aircraft flight control system 110 via the switching network 112 and the aircraft flight control network 111. The internal operation, power conversion and flight of the aircraft and control of the missile 102 are achieved by a switching network 112 and an aircraft flight power control network 111 that receive the aircraft flight control system 110.

The switch 140 is respectively connected with the airplane flight force control network 111 of the airplane flight control system 110 and the missile flight force control network 131 of the missile flight control system 130, and the switch 140 is connected with the missile power system 120 through the missile power network 121; the switch 140 selects the on-network missile power system 120 based on the switching network 112 provided by the aircraft flight control system 110. In operation, the switch 140 may respectively send the airplane flight control network 111 and the guided missile flight control network 131 sent by the airplane flight control system 110 and the guided missile flight control system 130 to the guided missile power system 120 via the guided missile power network 121.

Referring to fig. 1, the airplane flight control network 111 of the airplane flight control system 110 is connected to the missile power system 120, and when the airplane flight control network 111 of the airplane flight control system 110 is connected to the missile power system 120, the whole system works in the power propulsion state of the missile 102; the aircraft flight control system 110 controls the power of the guided missiles, the power of the guided missiles 102 is utilized to help the aircraft to take off quickly, and when the power of the aircraft per se fails, the power of the guided missiles 102 can help the aircraft to maintain the flying height in an emergency mode.

The missile flight control system 130 is connected with the missile power system 120 through a switch 140, when the missile flight control system 130 is connected into the missile power system 120 through a missile flight power control network 131, the whole system works in a missile autonomous flight mode, and at the moment, a missile is launched and is not connected with an airplane any more.

The switch 140 controls the network connection of the switching network 112, the airplane flight force control network 111, the missile power network 121 and the missile flight force control network 131, and the switch 140 realizes the network signal input and output of the switching network 112, the airplane flight force control network 111, the missile power network 121 and the missile flight force control network 131.

The power source of the missile 102 comprises solid fuel and liquid fuel, and also comprises power of a motor, an engine and the like. The missile 102 has wide power source distribution, on one hand, the wide and rich power source channel of the missile 102 is realized, and on the other hand, the foundation is provided for realizing the power diversification.

The utility model provides an aircraft system based on guided missile power advances, guided missile power advances the aircraft and comprises fuselage 100, wing 101 and the inside aircraft flight control system 110 of fuselage 100, guided missile driving system 120, guided missile flight control system 130 and switch 140. When the airplane flight control network 111 of the airplane flight control system 110 is connected to the missile power system 120 during operation, the whole system works in a missile power propulsion state; the aircraft flight control system 110 controls the power of the guided missiles, the power of the guided missiles 102 is utilized to help the aircraft to take off quickly, and when the power of the aircraft per se fails, the power of the guided missiles 102 can help the aircraft to maintain the flying height in an emergency mode. The utility model provides a power of guided missile generally only just starts when guided missile 102 launches, to the take-off and the flight of aircraft do not have helpful problem, with guided missile 102's power in addition, when the aircraft takes off, under guided missile 102's boosting, the aircraft can accelerate with the fastest speed to shorten the race distance of taking off. The utility model discloses a guided missile 102 passes through stores pylon 103 and connector 104 direct mount on wing 101 or fuselage 100, and guided missile 102 carry working method has two kinds when using, and a mode is fixed wing unmanned aerial vehicle carry work, and another kind of mode is many rotor unmanned aerial vehicle carry work. The two mounting working modes can fully meet different working requirements.

The above, only be the concrete implementation of the preferred embodiment of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art is in the technical scope of the present invention, according to the technical solution of the present invention and the utility model, the concept of which is equivalent to replace or change, should be covered within the protection scope of the present invention.

Claims (8)

1. The missile power propulsion-based airplane system is characterized in that the missile power propulsion-based airplane consists of a fuselage (100), wings (101), an airplane flight control system (110) inside the fuselage (100), a missile power system (120), a missile flight control system (130) and a switcher (140); the wings (101) are arranged on two sides of the fuselage (100), and the missiles (102) are arranged on the wings (101) or the fuselage (100); the missile (102) is fixed on the wing (101) and the multiple rotors (101-1) in a mounting working mode.

2. The missile power propulsion-based aircraft system as claimed in claim 1, wherein the missile (102) is mounted in a fixed wing unmanned aerial vehicle mode, and the missile (102) is directly mounted on the wing (101) through a hanging frame (103) and a connector (104).

3. A missile power propulsion-based aircraft system as claimed in claim 1, wherein the missile (102) is mounted in a mode of multi-rotor unmanned aerial vehicle mounting work, and the missile (102) is mounted on a multi-rotor (101-1) through a hanging rack (103) and a connector (104).

4. A missile-based power propulsion aircraft system as claimed in claim 1 wherein the switch (140) is connected to the aircraft flight control system (110) via a switching network (112) and an aircraft flight power control network (111).

5. A missile power propulsion-based aircraft system as claimed in claim 1, wherein the switch (140) is connected with an aircraft flight power control network (111) of the aircraft flight control system (110) and a missile flight power control network (131) of the missile flight control system (130), respectively, and the switch (140) is connected with the missile power system (120) through a missile power network (121); the switch (140) selects the network-connected missile power system (120) according to a switching network (112) given by the aircraft flight control system (110).

6. A missile power propulsion-based aircraft system as claimed in claim 1, wherein the aircraft flight power control network (111) of the aircraft flight control system (110) is connected with the missile power system (120), and when the aircraft flight power control network (111) of the aircraft flight control system (110) is connected with the missile power system (120), the whole system works in the missile (102) power propulsion state; an aircraft flight control system (110) controls the power of the missile.

7. A missile power propulsion-based aircraft system as claimed in claim 1, wherein the missile flight control system (130) is connected to the missile power system (120) through a switch (140) on the one hand, and the missile flight control system (130) is connected to the missile power system (120) through a missile flight power control network (131) on the other hand.

8. A missile power propulsion-based aircraft system as claimed in claim 1 wherein the switch (140) controls the network connections of the switch network (112), the aircraft flight power control network (111), the missile power network (121) and the missile flight power control network (131).

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