阅读说明：本技术 多向推力式发动机 (Multidirectional thrust type engine ) 是由 李晓亮 于 2021-09-09 设计创作，主要内容包括：本发明公开了一种包括机体(1)、正向推力部分(2)、消力部分(3)和反向推力部分(4)的多向推力式发动机；机体(1)、正向推力部分(2)和消力部分(3)为已有专利内容。当增加了反向推力部分(4)之后,关闭正向推力部分(2)后,起动反向推力部分(4),打开电磁阀(4-3)和水泵(4-1),水(2-7)进入水管(4-2)到喷管(4-4),从喷管(4-4)喷出射向管(3-4)喷出的水(2-7),从而使水(2-7)相碰,从而使喷管(4-4)喷出的水(2-7)速度减小；而向后推的力大于向前推力,飞机开始减速。当然,本发明如果在船舶、列车和汽车等产品上应用时,也可以向后方行驶。(The invention discloses a multi-direction thrust type engine which comprises an engine body (1), a forward thrust part (2), a force eliminating part (3) and a reverse thrust part (4); the machine body (1), the positive thrust part (2) and the force eliminating part (3) are the prior patent contents. After the reverse thrust part (4) is added, the forward thrust part (2) is closed, the reverse thrust part (4) is started, the electromagnetic valve (4-3) and the water pump (4-1) are opened, water (2-7) enters the water pipe (4-2) to the spray pipe (4-4), and the water (2-7) sprayed to the pipe (3-4) is sprayed from the spray pipe (4-4), so that the water (2-7) is collided, and the speed of the water (2-7) sprayed by the spray pipe (4-4) is reduced; and the force pushing backwards is greater than the force pushing forwards, the aircraft begins to decelerate. Of course, the present invention can be used for driving backward when applied to products such as ships, trains, automobiles, etc.)

1. A multidirectional thrust type engine comprises a machine body (1), a water pump (2-1), a water outlet pipe (2-2), an electromagnetic valve (2-3), a spray pipe (2-4), a bolt (2-5), a water pool (2-6), water (2-7), a water pump (3-1), a water outlet pipe (3-2), an electromagnetic valve (3-3), a jet pipe (3-4), a support (3-5) and a bolt (3-6); the water pool (2-6) is arranged on the machine body (1) through bolts (2-5), water (2-7) is placed in the water pool (2-6), the water pump (2-1) is placed in the water (2-7) and arranged on the support (3-5); the water pool (2-6) is arranged on the machine body (1) through a bolt (2-5), water (2-7) is placed in the water pool (2-6), the water pump (2-1) is placed in the water (2-7), one end of a water outlet pipe (2-2) is connected with the water pump (2-1), the other end of the water outlet pipe is connected with a spray pipe (2-4), the electromagnetic valve (2-3) is arranged in the middle of the water outlet pipe, and the spray pipe (2-4) is arranged on the water pool (2-6) through a bolt (2-5); the water pump (3-1) is placed in the water (2-7), one end of the water outlet pipe (3-2) is connected with the water pump (3-1), the other end of the water outlet pipe is connected with the jet pipe (3-4), the electromagnetic valve (3-3) is arranged in the middle of the water outlet pipe, the support (3-5) is welded at the top of the water pool (2-6), and the jet pipe (3-4) is arranged on the support (3-5) through a bolt (3-6); the method is characterized in that: the water pump (4-1) is placed in the water (2-7), one end of the water outlet pipe (4-2) is connected with the water pump (4-1), the other end of the water outlet pipe is connected with the spray pipe (4-4), the electromagnetic valve (4-3) is arranged in the middle of the water outlet pipe, and the spray pipe (4-4) is arranged on the water pool (2-6) through a bolt (4-5); when the airplane needs to decelerate in flight, the water pump (3-1) and the water pump (4-1) are opened, the electromagnetic valve (3-3) and the electromagnetic valve (4-3) are communicated, and the water pump (2-1) and the electromagnetic valve (2-3) are closed; water (2-7) flows into the water outlet pipe (4-2) from the water pump (4-1), water (2-7) flows into the water outlet pipe (4-2) from the water pump (4-1), enters the water outlet pipe (4-2) through the electromagnetic valve (4-3) and then flows towards the spray pipe (4-4), the spray pipe (4-4) sprays water (2-7) forwards, similarly, under the action of the spray pipe (3-4) spraying water (2-7), the speed of the spray pipe (4-4) spraying water (2-7) is reduced, the airplane is subjected to a backward force, and the forward speed of the airplane is reduced.

2. A multidirectional thrust type engine comprises a machine body (1), a water tank (2), water (3), a plunger pump (4), a front pipe (5), a support (8), a bolt (9) and a water inlet pipe (10), wherein the water tank (2) is arranged on the machine body (1) through the bolt (9), the water (3) is placed in the water tank (2), the support (8) is welded at the bottom of the water tank (2), one end of the water inlet pipe (10) is arranged on the plunger pump (4), and the plunger pump (4) is arranged on the support (8) through the bolt (9); one end of a front pipe (5-1) is connected with a plunger pump (4), the other end of the front pipe is connected with a front spray pipe (5-3), an electromagnetic valve (5-2) is arranged in the middle of the front pipe, and the front spray pipe (5-3) is arranged on a water pool (2-6) through a bolt (5-4); the middle pipe (6-1) is connected with the front pipe (5-1), the other end is connected with the middle spray pipe (6-3), the middle part is provided with an electromagnetic valve (6-2), one end of the frame (6-4) is welded on the water pool (2), and the other end is connected with the middle spray pipe (6-3) through a bolt (6-5); the method is characterized in that: one end of a rear pipe (7-1) is welded on the front pipe (5-1), the other end is welded on a rear spray pipe (7-3), the middle of the rear pipe is provided with an electromagnetic valve (7-2), and the rear spray pipe (7-3) is arranged on the water pool (2) by a bolt (7-4); when the flying water purifier is used, when the flying water needs to fly forwards, the plunger pump (4) is switched on, the electromagnetic valve (5-2) and the electromagnetic valve (7-2) are opened, water (3) is sucked into the water inlet pipe (10), enters the plunger pump (4), passes through the front pipe (5-1), flows through the front pipe (5-1) through the electromagnetic valve (5-2), enters the front spray pipe (5-3), and is sprayed out backwards through the spray pipe (5-3); on the other hand, water (3) enters the middle pipe (6-1) and the electromagnetic valve (6-2) through the front pipe (5-1) and then flows to the middle spray pipe (6-3) after entering the middle pipe (6-1), the water (3) is sprayed out from a downward hole of the middle spray pipe (6-3) and just sprays to the water (3) sprayed out from the front spray pipe (5-3), the water (3) sprayed out from the front spray pipe (5-3) is reduced in speed finally under the action of the water (3) sprayed out from the middle spray pipe (6-3), and the airplane flies forward; when the speed needs to be reduced or stopped, the electromagnetic valve (5-2) is closed, and the electromagnetic valve (7-2) is switched on, so that the rear spray pipe (7-3) can spray water (3), and the speed of the spray pipe (7-3) spraying water (3) to the rear can be reduced under the action of the water (3) sprayed from the middle spray pipe (6-3); the aircraft is subjected to a rearward force and the aircraft speed is reduced.

FIELD

The present invention relates to an engine for propelling an aircraft.

Background

Because the existing aircraft engines all use air at the back as a reaction force, the reaction force is small, the working efficiency is low, and the energy consumption is large; in contrast, the inventor proposes liquid as a reaction force in the previous period of time, and applies for Chinese patents with patent names of: hydraulic thrust driven engine, application number is: 202110979480.0. however, the new technology also has the problem of inconvenient braking.

Disclosure of Invention

The invention aims to solve the problems that: a method is found for braking and quickly steering the airplane during navigation.

In order to solve the above problems, the operating principle of the multi-directional thrust engine of the present invention is: the water pump is adopted to pump water and then spray the water backwards, and water is sprayed to the water sprayed backwards at the periphery of the water pump while the water is sprayed backwards, so that the engine generates forward pushing force; if the speed is reduced, the other water sprayed forwards can be started, and meanwhile, the water sprayed backwards is closed; in this case, the effect obtained is just opposite to the former. The engine generates a thrust-back force by which the aircraft begins to decelerate.

By adopting the method, when the airplane flies and an emergency occurs, the speed of the airplane can be reduced in a short time. Meanwhile, when the airplane is about to land, the speed of the airplane can be firstly reduced in the air and then the airplane starts to land, so that the sliding distance is very short.

Drawings

Fig. 1 is a structural view of a multi-directional thrust engine 1 according to an embodiment of the present invention.

Fig. 2 is a structural view of a 2 nd embodiment of the multi-directional thrust engine of the present invention.

Examples

In the embodiment 1 shown in the attached figure 1, the multi-direction thrust type engine comprises a body (1), a forward thrust part (2), a force eliminating part (3) and a reverse thrust part (4), wherein the forward thrust part (2) comprises a water pump (2-1), a water outlet pipe (2-2), an electromagnetic valve (2-3), a spray pipe (2-4), a bolt (2-5), a water pool (2-6) and water (2-7); the force eliminating part (3) comprises a water pump (3-1), a water outlet pipe (3-2), an electromagnetic valve (3-3), a jet pipe (3-4), a support (3-5) and a bolt (3-6); the thrust-absorbing water pump comprises a forward thrust part (2), a force-absorbing part (3) and a reverse thrust part (4), wherein the forward thrust part (2) comprises a water pump (2-1), a water outlet pipe (2-2), an electromagnetic valve (2-3), a spray pipe (2-4), a bolt (2-5), a water pool (2-6) and water (2-7); the force eliminating part (3) comprises a water pump (3-1), a water outlet pipe (3-2), an electromagnetic valve (3-3), a jet pipe (3-4), a support (3-5) and a bolt (3-6); the reverse thrust part (4) comprises a water pump (4-1), a water outlet pipe (4-2), an electromagnetic valve (4-3), a spray pipe (4-4) and a bolt (4-5); the water pool (2-6) is arranged on the machine body (1) through a bolt (2-5), water (2-7) is placed in the water pool (2-6), the water pump (2-1) is placed in the water (2-7), one end of a water outlet pipe (2-2) is connected with the water pump (2-1), the other end of the water outlet pipe is connected with a spray pipe (2-4), the electromagnetic valve (2-3) is arranged in the middle of the water outlet pipe, and the spray pipe (2-4) is arranged on the water pool (2-6) through a bolt (2-5); the water pump (3-1) is placed in the water (2-7), one end of the water outlet pipe (3-2) is connected with the water pump (3-1), the other end of the water outlet pipe is connected with the jet pipe (3-4), the electromagnetic valve (3-3) is arranged in the middle of the water outlet pipe, the support (3-5) is welded at the top of the water pool (2-6), and the jet pipe (3-4) is arranged on the support (3-5) through a bolt (3-6); the water pump (4-1) is arranged in the water (2-7), one end of the water outlet pipe (4-2) is connected with the water pump (4-1), the other end is connected with the spray pipe (4-4), the electromagnetic valve (4-3) is arranged in the middle, and the spray pipe (4-4) is arranged on the water pool (2-6) through a bolt (4-5). When the airplane flies forwards, the water pump (2-1) and the water pump (3-1) are switched on, the electromagnetic valve (2-3) and the electromagnetic valve (3-3) are opened, and water (2-7) enters the water outlet pipe (2-2) through the water pump (2-1) under the action of the water pump (2-1), flows into the electromagnetic valve (2-3), enters the spray pipe (2-4) through the water outlet pipe (2-2) and is sprayed out from the spray pipe (2-4) backwards; meanwhile, water (2-7) enters the water pump (3-1), enters the water outlet pipe (3-2), passes through the electromagnetic valve (3-3), passes through the water pipe (3-2), enters the injection pipe (3-4), is sprayed out from a hole formed downwards in the injection pipe (3-4), and is just collided by the water (2-7) sprayed out from the spray pipe (2-4), so that the water (2-7) sprayed out from the spray pipe (2-4) is impacted once when the water advances for one section, the speed of the water is relatively low, and the airplane runs forwards. When emergency braking is required, the power supply of the water pump (2-1) can be turned off, meanwhile, the power supply of the water pump (4-1) is switched on, the electromagnetic valve (4-3) is turned on, water (2-7) flows into the water outlet pipe (4-2) from the water pump (4-1), enters the water outlet pipe (4-2) through the electromagnetic valve (4-3) and then flows to the spray pipe (4-4), the water (2-7) is sprayed forwards by the spray pipe (4-4), similarly, under the action of the water (2-7) sprayed by the spray pipe (3-4), the speed of the water (2-7) sprayed by the spray pipe (4-4) is reduced, the airplane is subjected to a backward force, and the forward speed of the airplane is reduced.

In the 2 nd embodiment shown in the attached figure 2, the multidirectional thrust type engine comprises a body (1), a water pool (2), water (3), a plunger pump (4), a front pipe (5), a middle pipe (6), a tail pipe (7), a bracket (8), a bolt (9) and a water inlet pipe (10), wherein the front pipe (5) comprises a front pipe (5-1), an electromagnetic valve (5-2), a front spray pipe (5-3) and a bolt (5-4); the middle pipe (6) comprises a middle pipe (6-1), an electromagnetic valve (6-2), a middle spray pipe (6-3), a frame (6-4) and a bolt (6-5); the rear pipe (7) comprises a rear pipe (7-1), an electromagnetic valve (7-2), a rear spray pipe (7-3) and a bolt (7-4); the water pool (2) is arranged on the machine body (1) through a bolt (9), water (3) is placed in the water pool (2), a support (8) is welded at the bottom of the water pool (2), a plunger pump (4) is arranged on the support (8) through the bolt (9), one end of a water inlet pipe (10) is connected with the plunger pump (4), the other end of the water inlet pipe is placed in the water (3), one end of a front pipe (5-1) is connected with the plunger pump (4), the other end of the front pipe is connected with a front spray pipe (5-3), an electromagnetic valve (5-2) is arranged in the middle of the front pipe, the front spray pipe (5-3) is arranged on the water pool (2) through the bolt (5-4), one end of a middle pipe (6-1) is welded on the front pipe (5-1), the other end of the middle pipe is welded on the middle spray pipe (6-3), the electromagnetic valve (6-2) is arranged in the middle of the front pipe, one end of a frame (6-4) is welded on the water pool (2), the other end is connected with the middle spray pipe (6-3) through a bolt (6-5); one end of the rear pipe (7-1) is welded on the front pipe (5-1), the other end is welded on the rear spray pipe (7-3), the electromagnetic valve (7-2) is arranged in the middle, and the rear spray pipe (7-3) is arranged on the water pool (2) through the bolt (7-4). When the flying water purifier is used, when the flying water needs to fly forwards, the plunger pump (4) is switched on, the electromagnetic valve (5-2) and the electromagnetic valve (7-2) are opened, water (3) is sucked into the water inlet pipe (10), enters the plunger pump (4), passes through the front pipe (5-1), flows through the front pipe (5-1) through the electromagnetic valve (5-2), enters the front spray pipe (5-3), and is sprayed out backwards through the spray pipe (5-3); on the other hand, water (3) enters the middle pipe (6-1) and the electromagnetic valve (6-2) through the front pipe (5-1) and then flows to the middle spray pipe (6-3) after entering the middle pipe (6-1), the water (3) is sprayed out from a downward hole of the middle spray pipe (6-3) and just sprays the water (3) sprayed out from the front spray pipe (5-3), the water (3) sprayed out from the front spray pipe (5-3) is reduced in speed finally under the action of the water (3) sprayed out from the middle spray pipe (6-3), and the airplane flies forward. When the speed reduction or stop is needed, the electromagnetic valve (5-2) is closed, the electromagnetic valve (7-2) is switched on, so that the rear spray pipe (7-3) can spray water (3) at the same time, and the speed of the spray pipe (7-3) spraying water (3) to the rear can be reduced under the action of the water (3) sprayed from the middle spray pipe (6-3). The aircraft is subjected to a rearward force and the aircraft speed is reduced.

The invention is not limited to the above forms, in the embodiment 1, when the water pump (2-1) and the water pump (3-1) are combined into one water pump; in the embodiment 2, the plunger pump (4) is three independent water pumps which are respectively used for supplying water to the front spray pipe (5-3), the middle spray pipe (6-3) and the rear spray pipe (2-7); when the speed reducer is applied to other products such as ships, automobiles, trains and the like, the speed reducer can be used for speed reduction or parking, and meanwhile, the speed reducer can also be used for backward running. The invention also provides a new form formed by combining the forms.

When the speed reducer is applied to other products such as ships, automobiles, trains and the like, the speed reducer can be used for speed reduction or parking, and meanwhile, the speed reducer can also be used for backward running.

The invention also relates to a method for turning the airplane, which is characterized in that the two sides of the airplane are symmetrically distributed, the thrust of one side is reduced, and the airplane can achieve the purpose of turning.