CN100422044C - Solar controllable buoyancy, self-control stable helium blue sky spacecraft - Google Patents

Abstract

The present invention is a solar controllable buoyancy, self-control stable and balanced helium blue sky spacecraft, equipped with a buoyancy device, a power device, a manned or a manned and loaded device, a buoyancy device and a buoyancy control device that are lighter than air to generate buoyancy There are two groups of buoyancy gas containers—soft balloons or soft and hard balloons. Different balloon groups are connected by pipelines. Pressure pumps, namely air pumps and inflation and deflation valves are connected in series on the pipelines, and buoyancy is generated by inflatable balloons. Under the pressure of the inflator pump, the gas realizes different pressure and density distributions in different balloon groups, thereby automatically controlling the buoyancy; buoyancy control is to use electronic control systems or computer programs to control and adjust the different densities and pressure distributions of buoyancy gas between balloons in each group Realized; be provided with and realize self-control stable balance " regulate and control flight air flow air pump ", its air outlet end leads to the air outlet that is distributed in the position around the aircraft through the air outlet pipeline and branch pipe, the present invention is cheap, energy environmental protection, safety is good.

Description

Solar controllable buoyancy, self-control stable helium blue sky spacecraft

1. Technical field

The invention belongs to the balloon aircraft technology—airship technology in the field of aviation technology, in particular to a solar controllable buoyancy, self-control stable and balanced helium blue sky spacecraft.

2. Background technology

The earliest implementation of balloon aircraft can be traced back to 1784, the test flight of the human-propelled fish-shaped hydrogen-filled flying boat of the French Robert brothers. In 1852, French engineer Giffard designed and manufactured a steerable hydrogen-filled airship with an airbag of 2,500 cubic meters and a propeller driven by a steam engine. Later, soft balloon airships were replaced by rigid airships with metal and wood frames covered with skins. By the beginning of the 20th century, airship technology was becoming more and more mature. The German inventor Zeppelin made important contributions, making airship aviation the leading trend of the world's aviation industry at the beginning of the 20th century. From 1910 to 1914, Germany's Draig airship airline achieved a performance of 2.14 million kilometers of airship sailing and safely carrying 35,000 passengers. The Hindenburg airship successfully manufactured in Germany in 1936 is 245 meters long, 41 meters in diameter, with a total airbag volume of 200,000 cubic meters and a total weight of 230 tons. It is powered by four 610-kilowatt engines and can carry 75 passengers. Km/h, the battery life is 200 hours, the luxury of interior decoration and the comfort of equipment are no less than that of the "Titanic" luxury liner. The boat made a total of 63 commercial flights. In the First World War, airships were also widely used in military affairs by various countries, and achieved outstanding results.

However, the end of the airship aviation industry was also marked by the sudden fire and explosion of the Hindenburg spacecraft when it landed in New Jersey, USA on May 6, 1937. However, it is not accidental that airship aviation was replaced by emerging aircraft aviation. Its inevitability lies in the two major defects of inflatable airships at that time: one is that the gas inflated by most airships is flammable and explosive hydrogen; Not strong enough to withstand a storm. Especially when civil and military aviation are increasingly pursuing the needs of high speed targets, airships are even more unable to compete with aircraft.

In the era of the rise of aircraft aviation and the complete occupation of the aviation industry, from the 1970s, the inflatable aircraft—airship aviation began to recover again. On the one hand, this is because new material technology and control technology can improve the defects of airships in history, so that airships have the ability to compete with aircraft aviation in terms of load capacity, shipping cost, and safety; the more important deep-seated reasons are: The shortage of energy and oil in the world is becoming more and more serious, and the aircraft and aviation industry, which consumes huge amounts of oil, is also facing a serious crisis. Once the oil is exhausted, all existing aircraft will become a pile of waste.

The recovering inflatable airship has not developed fast for decades, and it is far from entering civil aviation and other practical aviation fields in large numbers, because there are still some shortcomings in safety and practicality, especially the flexibility to control the movement in all directions in the air It is not yet perfect, and the energy consumed is still basically petroleum products.

3. Contents of the invention

The purpose of the present invention is exactly to design and manufacture a kind of air-filled aircraft that is safer, more economical, and more flexible than existing similar products, so that it has stronger competitiveness for aircraft aviation in practical applications: its air accident rate is far lower Compared with the existing aircraft aviation, the cost of passenger and cargo is much lower than that of air transportation, and it can also be compared with air transportation in terms of transportation efficiency and practicability; thus it has the conditions to enter the civil aviation industry in large numbers and become a household aircraft popularized by the public. The aircraft referred to in the present invention is a new airship that has significant technical updates compared to existing airships in history—the airship is also called the blue sky airship in the present invention. Because ship and boat are synonymous words, adding the word "blue sky" in front of it means that it sails in the atmosphere, which is different from the currently popular appellation of spaceship.

Solar controllable buoyancy, self-control stable and balanced helium blue sky spacecraft, equipped with buoyancy device, power device, manned or manned and loaded device with buoyancy generated by lighter-than-air balloons; power device: propeller or airflow driven by electric motor or internal combustion engine The pump jet is the power; buoyancy device and buoyancy control device: at least two sets of buoyancy gas containers—soft balloons or soft and hard balloons are provided. The pump and the inflation and deflation valve rely on inflatable balloons to generate buoyancy, and the buoyancy gas realizes different pressure and density distributions in different balloon groups under the pressure of the inflator pump, thereby automatically controlling the buoyancy; the lower part of the buoyancy device is connected to manned or manned and loaded objects The container and the buoyancy control device are buoyancy control devices that use electronic control systems or computer programs to control and adjust the different densities and pressure distributions of buoyancy gas between balloons; Air pump", its air outlet leads to the air nozzles with adjustable air volume valves distributed around the aircraft through the air outlet pipe and branch pipe, and its air inlet leads to the air inlet opening to the outside through the air inlet pipe; There is an electronic control system or computer program to control the distribution and intensity of the airflow ejected to the outside world by the "control flight airflow pump"; the buoyancy gas container balloons are all soft balloons made of elastic membranes, and these balloons are divided into groups. That is, the main balloon group A, the main balloon group B and several groups of auxiliary balloons; each group of balloons is composed of several balloons, referred to as unit balloons, and the unit balloons are connected to the main trachea by a lung tube type trachea similar to the animal lung trachea; There are two sets of tubular trachea and main trachea, one is the inflatable trachea and the other is the exhaust trachea; there are three types of motors in the power unit, namely the air pump motor for inflating between the main and auxiliary balloons, and the propeller thruster The electric motor that drives the electric motor that produces the air pump that "regulates the flight airflow"; the balloon cabin space that accommodates all the balloons has a flat shape, with a large flat roof, solar cells are installed on the flat roof, and batteries and small internal combustion generators are set as backup Power supply; all the connections between the end of the bronchi and the balloon are connected by the valve core of chicken intestine; the outlet of the valve core is inside the balloon when the air enters the balloon; the outlet of the valve core is outside the balloon when the air flows out of the balloon; the inlet of the air pump is also There is a branch pipe with a controllable air valve, which is used as a pipe for the intake of external air source.

In the present invention, the purpose of allocating gas between the main balloon and the auxiliary balloon is to regulate the buoyancy gas volume compatible with the flight altitude. The automatic control of flight motion stability is achieved by using an electronic control system or computer program to control the operation of the propeller driven by the motor and the distribution and intensity of the airflow injected by the airflow pump to the outside.

The invention is a kind of electric energy converted by solar energy as the energy source of the power motor, relying on the helium-filled balloon to generate buoyancy, which can control the buoyancy according to the flight needs and automatically control the flight stability, and is manned or manned in the atmosphere. payload aircraft;

The electricity required for the operation of the aircraft and the operation of the power motor is supplied by solar cells. Another storage battery and a small internal combustion generator set are used as backup power sources.

The "regulating and controlling flight airflow air pump" of the present invention is characterized in that: its air outlet leads to the air nozzles distributed in various directions of the aircraft with adjustable air volume valves through the air outlet pipe and branch pipe; its air inlet The end leads to the air inlet opening to the outside through the air inlet duct. Air nozzles with adjustable air volume valves are arranged around the aircraft. Its outlet end leads to air nozzles with adjustable air volume valves distributed around the aircraft through outlet pipes and branch pipes. Its air intake end passes through air intake pipes. It leads to the air inlet opening to the outside; its self-control and stability is achieved by using an electronic control system or a computer program to control the distribution and intensity of the airflow ejected to the outside by the "regulating flight airflow air pump".

When the converted electric energy with solar energy is the main power or energy source, the power motor of the present invention is characterized in that: the power motor has three kinds, i.e. the air pump motor (hereinafter referred to as the air-charge motor) inflated between the main and auxiliary balloon groups, The motor that drives the propeller (hereinafter referred to as the propulsion motor) drives the motor that generates the air pump that "regulates the flight airflow" (hereinafter referred to as the airflow motor).

Aircraft of the present invention is characterized in that its structure is made up of pipe frame and sheet material or film skin, and the frame or skeleton that metal or plastics or composite material are made and covers skin is made rigid type airship. And form 3 cabins connected as one, i.e. balloon cabin, engine room, cockpit, soft balloon is placed in the hard balloon cabin.

Aircraft of the present invention is characterized in that: it is equipped with the propeller propeller that is fixed on " the frame shell of aircraft " or " the auxiliary structure that is connected with aircraft frame, shell ".

The aircraft of the present invention is characterized in that it is equipped with an automatic control system or a computer and ancillary control system equipped with special programs, as the control equipment for automatically controlling the charging motor, propulsion motor, airflow motor and each controllable air valve.

The air pump of the present invention allocates gas between two groups of main balloons for regulating and descending, and allocates gas between the main balloons and secondary balloons for regulating the volume of buoyant gas adapted to the flight altitude.

The effect that the present invention increases compared with prior art is as follows:

(1) It will bring a kind of air transportation with the highest security at present. It is supported by dozens or more unit balloons, and it is impossible for any serious air accidents to occur unless bad weather occurs. The close communication link with the weather information center allows it to avoid severe weather. This has an important appeal to people in the contemporary era where air accidents are frequent.

(2) It will solve the deadly threat of the oil energy crisis to the aviation industry. It uses natural buoyancy to greatly reduce energy consumption; it uses solar energy to reduce fuel consumption to zero.

(3) Its perfect adjustable buoyancy system, automatic control system for flight stability and other automatic control systems, and strong and lightweight new materials make it more flexible, stable, and structurally safer than previous helium-filled airship.

(4) It will be possible to provide a brand-new aerial home aircraft, and it will be possible to change the era of home cars into the era of home blue sky spaceships, thereby providing modern people with a new way of life and meeting the increasingly updated needs of modern people ; And thus promote the development of related industries.

(5) Its flying speed is expected to exceed that of a car. It can be lifted and lowered in elevated airports or high-rise buildings without occupying ground space. The gap between it and the existing aircraft speed can be made up by shortening the distance between the airport and the origin and destination.

(6) It has a soft air cushion at the bottom of the cockpit, which can better protect the ground from accidental damage, and can also land safely and float safely on the water.

(7) Its balloon cabin roof can also use a small part of the area to serve as a crew sightseeing deck except that solar cells are installed; the crew can obtain the incomparable air-flight experience of existing aircraft. The "deck" can also be used by passengers wearing seat belts to "land" in the air and walk up dangerous peaks, which will bring a new way of air travel.

(8) In addition to solar energy, it is also equipped with battery and external power charging interface, which can meet the needs of low-speed sailing and return without the sun; it has a small internal combustion generator set as a backup power supply, which increases the reliability of the circuit and control system . Its balloon has a manual emergency deflation port, and it can land safely even in extreme power failure situations.

In a word, the characteristic effect pursued deliberately by the idea of the present invention is:

The joy of embracing the blue sky, cheap and environmentally friendly energy, and foolproof safety.

4. Description of drawings

Fig. 1 is the appearance of the present invention: in the figure, 1 is a solar cell; 2 is a balloon cabin; 3 is a cabin; 4 is a cockpit; 5 is a wing; 6 is a propeller propeller; Cone; 9 is tail rudder.

Fig. 2 is a front view of the appearance of the present invention.

Fig. 3 is a bottom view of the appearance of the present invention.

Fig. 4 is a "unit control circuit diagram" using fixed electronic control circuits instead of a computer program. IC in the figure is an integrated circuit - a circuit of a voltage comparator (-, + are its two input ports, o is its output terminal), U1 is the sensing signal or driving command signal, U0 is the reference signal or comparison signal, R1 Is the current limiting resistor, R2 is the voltage divider resistor, R3 is the input resistor, C is the input stabilization capacitor, BG is the triode; JG is the solid state relay; E+, E0 are the operating power. Control units or subsystems (complex control units) include: driving speed fine-tuning control unit, driving speed gear control unit, driving direction control unit, driving height fine-tuning control unit, driving height gear control unit, speed stability control subsystem, direction Stable regulation subsystem, highly stable regulation subsystem, horizontal stability regulation subsystem, solar battery regulation subsystem, battery regulation subsystem. The principle of the control unit is: when |U1|>|U0|(U1<U0=, the o terminal of the IC outputs a high level, BG has an input, it is amplified by BG, J is turned on, and one or more actuators are started. Generate execution actions (such as motor speed change, charge and discharge, selection switch).

Fig. 5 is a schematic diagram of the helium pipeline of the present invention. 10, 11, 12 are main air chamber A, main air chamber B, and auxiliary air chamber respectively, 13 is a controllable air valve, 14 is an air pump, and 15 is a helium external air source supply main pipe.

Fig. 6 is a schematic diagram of the pulmonary tube-type tracheal system, 16 is the common trachea, 17 is the first-order bronchi, 18 is the second-order bronchi, and 19 is the third-order bronchi. The number of stages can be set according to specific conditions. The bottom bronchus (terminal bronchi) connects the unit balloon, and 20 is the cut-off valve of the bottom bronchi that can be opened and closed automatically, and the opening and closing of the cut-off valve is controlled by the aircraft automatic control system and driving instructions. Each unit balloon is equipped with an air sensor sensitive to a certain concentration of air component gas. The principle of controlling the opening and closing of the cut-off valve (20) is: the air pressure of each balloon inflated and deflated by the same group of balloons should be even; This information controls the terminal bronchi cut-off air valve (20) of the balloon to be closed through the automatic control system, so as to stop the inflation and deflation flow of the balloon.

5. Specific implementation

Embodiments of the present invention are as follows (can refer to accompanying drawing 1 to accompanying drawing 6 of description):

Buoyancy regulation: realized through different densities and pressure distributions between two groups of balloons; it is carried out by setting height or ascending and descending commands, that is, by setting height or ascending and descending commands to control the inflation between the primary and secondary balloons The pump motor works and the balloon inflates and deflates time. Altitude control information can be obtained through adjustment methods such as altitude sensors and PID.

Equally, its self-control stability is to use above-mentioned inclination sensor to control the distribution and the intensity of the airflow ejected to the outside by the electronic control system or computer program. That is, the electronic control system or computer program is used to control and adjust the "regulating flight airflow air pump" that realizes self-control and stability, and promotes the regulating flight airflow air pump motor to generate the regulating flight airflow. The air outlet end of the air pump for regulating the flight air flow leads to the air nozzles with adjustable air volume valves distributed around the aircraft through the air outlet pipe and the branch pipe; its air inlet end leads to the air inlet opening to the outside through the air inlet pipe

The shape of the balloon cabin is an inverted billiard table with an upper diameter of 30 meters, a lower diameter of 6 meters and a thickness of 5 meters; solar cells are laid on the roof of the balloon cabin, and the maximum output power is 50-60 kilowatts; the bottom of the balloon cabin is 5 meters long from the top and 4 meters long from the bottom The cabin is connected with a cabin that is 2 meters wide and 1 meter high; the lower bottom of the cabin is connected with the cockpit that is 4 meters long at the top, 3.5 meters long at the bottom, 2 meters wide and 2 meters high. The bottom of the cockpit is along the first 3 meters of the length, and a soft air cushion bag with the same length and width as the bottom of the cockpit and a height of 0.5 meters is attached. The two ends of the cabin and the cockpit along the length direction are respectively defined as the front end and the rear end of the aircraft (the meanings of "front" and "rear" in this specification are consistent with this). The connecting surfaces between the front and rear ends of the upper roof of the cabin and the front and rear sides of the balloon cabin, the connecting surfaces between the upper roof and the lower bottom of the cabin, and the connecting surfaces between the upper roof and the lower bottom of the cockpit are all smooth curved surfaces; the front and rear ends of the upper roof of the cabin The upper edge of the transitional surface connecting the front and rear sides of the balloon cabin extends to the 10-meter-diameter section of the balloon cabin. In addition, on the basis of the above structure, the cabin and the cockpit are additionally made with a tapered tail that extends backward along the length direction and is 1 meter long (the extended transition surface at the upper part of the rear end of the cabin is no longer extended backward); The rear edge of the tapered tail is equipped with a tail rudder that can be controlled by electric signals.

The balloon cabin, engine room, and cockpit are made of carbon fiber composite material pipes or aramid fiber composite material pipes to make an integrated overall skeleton, and the panels of the same material are used as the outer walls of the engine room and cockpit. The surface of the balloon cabin and the interval between compartments are made of polyester film or other High-strength film is used as the skin. Part of the roof of the balloon cabin is covered with panels. The structural materials of the aircraft are all flame-retardant and fire-resistant materials or have been treated with flame-retardant and fire-proof treatments.

Along the cabin, the cockpit width direction, from the cabin, cockpit left and right side respectively stretch out the 2 meter long wing, also make its skeleton, shell by the same material as cabin skeleton, outer wall. The end of the wing is connected with the side of the balloon cabin through a transition surface. The wing is 0.3 meters thick and 1 meter wide, and the front and rear parts of the cross section are curved and smoothly connected with the upper and lower parts (the cross section becomes the streamlined shape of the aircraft wing). The length of the wing is perpendicular to the length direction of the cabin and the cockpit, the center plane of the width of the wing is aligned with the center plane of the length of the cabin, and the center plane of the thickness of the wing is aligned with the interface between the cabin and the cockpit. Elevators that can be controlled by electrical signals are installed behind the two wings.

The left and right wings are respectively equipped with a propulsion motor and a propeller propeller driven by it. The propeller is made of carbon fiber or aramid fiber composite material (can be a hollow shell structure). The propeller is in the front, and the motor and its propeller are placed in the cylindrical engine room of the left and right wings; the engine room is embedded in the center of the left and right wings along the length of the wing, and is connected to the surface of the wing through a smooth transition surface. The tail end of the engine compartment is tapered. The frame and skin materials of the engine compartment are the same as those of the wings. The rotating diameter of the propeller is 1.4 meters to 1.8 meters, and the power of each propeller motor is 15 kilowatts to 20 kilowatts. Left and right engine rooms to left and right wings along the front, rear, top and bottom positions of the wing section between the long and far ends of the wing and on the transition surface where the wing end is connected with the balloon cabin, each is provided with a belt that can The air nozzles of the air control valve (two wings, 10 wing air nozzles in 5 directions). The other ends of the controllable air valves of the left and right air nozzles of the wing are connected with the regulating airflow pipes of the left and right wings, and the left and right regulating airflow pipes converge and lead to the air pump for "controlling flight airflow" (airflow pump for short) in the cabin. ) of the air outlet; the air inlet of the airflow pump is led to the air inlet by the pipeline, and the air inlet is opened at the front end and the rear end of the cabin, and is switched by a controllable air valve.

The center of the roof of the balloon cabin; the transitional surface connecting the front and rear sides of the balloon cabin with the front and rear sides of the engine room; there is also a nozzle with a controllable air valve (there are 3 nozzles in total on the top of the balloon cabin and the side nozzles) , are respectively connected with the respective control air jet pipelines, and each jet pipeline leads to the air outlet of the air flow pump after converging. The two air inlets of the airflow pump are also made into air nozzles, and the air intake or jet is switched by the controllable air valve of the airflow pump. The air nozzle on the top of the balloon cabin sprays upwards, and the front and rear air nozzles on the sides of the balloon cabin spray downwards.

The motor or engine power of the airflow pump is 15 kilowatts to 20 kilowatts, and the air outlet end of the airflow pump is also connected with the small trachea of the exchange air in the supply cabin.

The balloon cabin is divided vertically from top to bottom into the main balloon group A cabin, the main balloon group B cabin and the auxiliary balloon cabin. The volume of these three balloon cabins is one-third of the total volume of the balloon cabin.

The total volume of the balloon cabin is 24693 cubic meters:

The volume of the main balloon A cabin B and the auxiliary balloon cabin is 8231 cubic meters, which is taken as 8000. Each of these three balloon sub-compartments can accommodate 27 unit balloons. Their inflated volumes are equal. Most of the balloons are inflated. It is cube-shaped, and the shape of the balloon near the boundary of a small number of subdivisions can be irregular with the boundary. The unit balloon membrane is made of high-strength, high-elasticity and low-density film material. Each balloon sub-compartment is equipped with in-cabin support components (used as pipes) to ensure the mechanical strength of the cabins; it is also equipped with balloon installation components separating the space of the balloon unit (used as thinner pipes), and each unit The balloons are all hung on the components at the top of the corresponding partitioned spaces. A part of the unit balloon has an emergency deflation nozzle that is strictly sealed at ordinary times and can be manually opened in case of emergency. Each balloon subdivision has a square cross-section channel in the center of the horizontal direction. All the channels are connected as a whole and enter the cabin. The opening on the top of the cabin is used as a space for pipelines, circuits, and personnel to pass through; the channels are separated by longitudinal intervals. Pipelines, circuits and personnel pass through the channel (hereinafter referred to as the channel). There are doors that open into the passage between the passage and each cabin and sub-cabin.

The soft airbag at the bottom of the cockpit is a soft airbag whose upper end is fixed on the bottom of the cockpit. It has a volume of 3×2×0.5=3 cubic meters and accommodates two layers of 8 rectangular unit air bags. They are connected with an air pump similar to a balloon group. The air duct system is connected to the airflow pump through the lung duct type air duct system and the controllable air valve of the main pipe; the air duct system is also divided into an inflatable duct system and an exhaust duct system, and the main air duct bypasses the interlayer at the rear of the cockpit and enters the cabin.

The connection between the non-integral components of the aircraft structure is mainly connected by rivets, and a few connections are connected by bolts when necessary. The component density of the aircraft structure, the section of the component pipe, the section of the structural skin, the section of the rivet and the bolt are all determined by the aircraft load (static load, dynamic load, accidental distributed load) and the mechanical properties of the material, and are determined by engineering mechanics calculations. The total static load of the aircraft does not exceed 1480 kg.

The top of the balloon cabin can also be used as a deck for the crew to visit. There are remote control automatic lifting guardrails on the edge of the deck, and all boarders are equipped with safety belts to fix on the "deck".

The main equipment in the engine room includes airflow pump, air pump, air valve, battery pack, control cabinet equipment, communication equipment, computer and air conditioner. The air pump electric motor power is 1 kilowatt to 3 kilowatts. The battery pack has a capacity of 30 kWh to 50 kWh and a weight of no more than 120 kg. The air conditioner uses two branch trachea drawn from the airflow pump piping system to take in and out the air.

The aircraft of the present invention is also equipped with the following sensing devices: front and rear, left and right horizontal inclination sensors (typically adopting a connecting pipe liquid level relay), flight speed and direction sensors, several acceleration sensors (using stress-sensitive materials to convert the stress generated by acceleration It is an electrical signal), a number of distance sensors from the height of the ground or adjacent obstacles in all directions (using laser ranging or ultrasonic ranging devices), a number of ambient air pressure and wind speed sensors (the wind speed sensors are installed at the wing end and connected to the balloon cabin section, cabin front end, tail end, etc.), a number of environmental electrostatic sensors, electromechanical equipment status sensors, and a number of external camera recording heads. The height sensor typically adopts a pressure sensor (altimeter), and is also equipped with GPS and electronic map.

The front part of the cockpit is the driving position, and the basic equipment for the pilot to operate is the steering wheel (uplift the steering wheel, press down to control the aircraft’s ascent and descent movement), and set its ascent and navigation altitude through the altimeter, the general navigation altitude is 1000-3000 meters, the control panel There are: multiple control keys, speed control handwheel (multi-purpose switch), instrument and foot brake, several flat panel display screens, video heads, microphones, speakers; there are computer keyboards and mice that can be drawn out in the control screen drawer.

Items in the cockpit should be made of non-metal elastic materials as much as possible. The interior volume of the cockpit (not including the tapered tail) is 2.5 meters long, 1.8 meters wide and 1.8 meters high. Three rows of seats are arranged along the length direction. The front row is the driver's seat and the flip-up seats on both sides. The middle row is a passenger seat and a flip-up seat; the rear row is a sleeping seat, and the bottom of the sleeping seat is a storage box for food, water, faucet, high-altitude work clothes and other appliances. The backrest of the middle row seat has the same structure as the front side panel under the seat, and can be turned into a backrest (with an extended backrest that can be opened and stowed corresponding to the flipped up seat), side panels, and bed panels. Can move forward and backward as a whole. There are tabletops that can be turned up on the left and right walls of the cabin. The cockpit is sealed, and the internal connection and exhaust holes of the air conditioner are opened at the front and rear ends of the cockpit roof. There is a door behind the rear seat that leads to the part of the space at the conical tail of the cockpit. Through the door, you can enter the toilet and toilet in the conical tail space of the cockpit (1 meter long, 1.8 meters high, and the width shrinks from 2 meters to zero). Discharge directly into the air. The bathroom door and the toilet should be at both ends of the width direction. The spare small internal combustion generator (capacity is about 1 kW to 3 kW), the fuel tank penetrates from the tail cone space of the engine room to the tail cone space of the cockpit, and the oil inlet pipe opens at the bottom of the tail cone of the cockpit (width center); Charging power and water supply are also connected here. The cockpit is equipped with a ladder.

The aircraft of the present embodiment adopts the computer of equipment special-purpose application software to control (but the electrical equipment is backed up again without the direct control system of computer), and actuator adopts multistage solid-state relay, uses between solid-state relay and computer I/O interface. Special encoder (integrated circuit), decoder (integrated circuit), channel connection. The terminal solid state relay controls each electric motor, each electric controllable air valve, and each servo micromotor for auxiliary manipulation. All kinds of sensor signals adopt information processor, and the information processing circuit that converts analog information into digital signal becomes digital signal, and then enters the computer I/O interface after being encoded by the encoder. Encoders, decoders, information processors, and solid-state relays are all in the control cabinet. By comparing the altimeter (typically a barometer) with the altitude set by the operation, the air pressure distribution of the balloon is controlled (the gas is put into the free-expanding balloon when floating, and pressurized into the pressure sphere on the contrary) to control the altitude of the spacecraft. drop.

The aircraft of the present invention is equipped with a radio remote controller, and the remote controller can replace the driving control equipment so that the driver can perform driving operations in any part of the aircraft.

The main control system of driving control and automatic control of the present invention is as follows:

(1) Speed control: The pilot's flight speed command (or preset program) and the sensor's flight speed information are transformed into speed regulation commands (acceleration, deceleration, stop) of the propulsion motor.

(2) Direction control: the pilot's flight direction command (or preset program) and the sensor's flight direction information are converted into rudder movement commands.

(3) Straight-line self-control: The acceleration information of the sensor is converted into the differential speed regulation command of the left and right propulsion motors (to achieve stable straight-line flight)

(4) Altitude control: The pilot's flight altitude command (or preset program) and the sensor's flight altitude information are transformed into the start command of the inflatable motor and the opening and closing commands of the corresponding controllable air valve.

(5) Stable self-control: The flight tilt information and wind speed information of the sensor are transformed into the starting command of the airflow pump, the opening and closing command of the corresponding controllable air valve (realizing stable flight) and the horizontal rudder movement command.

(6) Avoidance (also divided into avoidance and braking) self-control: the information from the sensor to the obstacle (including the ground) and the set safety distance information are transformed into the start-up speed regulation instructions of the propulsion motor, the airflow pump and the air pump and the corresponding possible parameters. The switch instruction of the air control valve is a reasonable modification instruction to the original movement speed and direction. When the driving command and the direct control command of the electrical equipment are inconsistent with the avoidance command, the control system mechanism guarantees to obey the latter.

(7) Electrical equipment current, voltage, thermal protection, and other automatic control systems for safety protection.

(8) Unmanned automatic flight control:

When there is no driving command, the driving command channel is automatically switched to the automatic flight information setting device (also a kind of information processor). At this time, the aircraft flies according to the original direction, speed and altitude and performs straight-line self-control, stable flight self-control and avoidance self-control . If the direction, speed, and altitude drift, there are two ways: eliminate the drift and follow the drift.

This embodiment is suitable for carrying 4 to 5 passengers (the total weight of passenger and cargo is no more than 300 kilograms), and the flight altitude is below 3000 meters.

The present invention can also have other embodiments, such as: increase the overall size and power, increase the carrying capacity; increase the equal-volume auxiliary balloon subdivision and the number of auxiliary balloon groups 1, 2, so that the flight height is increased to 7000 meters, 10 thousand meters or so. It can also reduce the overall size and power to make a single-person aircraft. For added safety, airbags can also be installed in the cockpit. The present invention can also have embodiments adopting other appearance shapes different from those of the foregoing embodiments. The exterior shapes of all the embodiments of the present invention should also be adjusted after aerodynamic calculations and tests.

Adopting fuel oil of the present invention is energy source, adopts internal combustion engine to be engine and embodiment as follows:

The gas cabin diameter is 20 meters, and height is 5 meters, and all the other dimensions are the same as the aforementioned embodiment using solar energy. The gas cabin is laid with a small amount of solar cells. The storage battery exceeds 20 kg and 10 kWh. The engine (propulsion engine) of left and right propellers is mostly 20-30 horsepower 4-stroke internal combustion engine, and they each drag a self-use electric generator. The air pump power machine is a 3-5 kilowatt motor. The airflow pump is powered by the propeller engine, and the air in and out is controlled by the self-control air valve. When the airflow is not required to control the flight, the air outflow of the air pump leads to the propeller facing the rear of the wing. The rest of the structure is the same as the aforementioned solar energy embodiment. Its total load height can exceed 900 kg, passenger cargo does not exceed 200 kg, and 2-3 passengers.

Claims (4)

1. Solar controllable buoyancy, self-control and stable helium blue sky spacecraft, equipped with buoyancy device, power device, manned or manned and loaded device with lighter-than-air balloon to generate buoyancy; power device: propeller driven by electric motor or internal combustion engine Or airflow pump jet as power; buoyancy device and buoyancy control device: at least two groups of buoyancy gas containers—soft balloons or soft and hard balloons are provided. Different balloon groups are connected by pipelines, and pressure pumps, pressure pumps, That is, the inflatable pump and the inflation and deflation valve rely on inflatable balloons to generate buoyancy, and the buoyancy gas realizes different pressure and density distributions in different balloon groups under the pressure of the inflator pump, thereby automatically controlling the buoyancy; the lower part of the buoyancy device is connected to manned or manned and combined The loading container and the buoyancy control device are buoyancy control devices that use electronic control systems or computer programs to control and adjust the different densities and pressure distributions of buoyancy gas between balloons; Airflow air pump", its air outlet leads to the air nozzles with adjustable air volume valves distributed around the aircraft through the air outlet pipe and branch pipe, and its air inlet leads to the air inlet opening to the outside world through the air inlet pipe. It is equipped with an electronic control system or a computer program to control the distribution and intensity of the airflow ejected to the outside by the electronic control system or computer program; the buoyancy gas container balloons are all soft balloons made of elastic membranes, and these balloons are divided into multiple types. Groups, that is, the main balloon group A, the main balloon group B and several groups of auxiliary balloons; each group of balloons is composed of several balloons, referred to as unit balloons, and the unit balloons are connected to the main trachea by using a lung tube type trachea similar to the animal lung trachea There are two sets of lung tube type trachea and total trachea, one is an inflatable trachea, and the other is an exhaust trachea; there are three types of motors in the power unit, that is, the air pump motor that inflates between the main and auxiliary balloons, and the propeller that pushes the air. The electric motor of the thruster drives the electric motor of the air pump that "regulates the flight airflow"; the space of the balloon cabin that accommodates all the balloons has a flat shape, and has a large-area flat roof on which solar cells, batteries and small internal combustion generators are installed As a backup power supply; all the connections between the end of the bronchi and the balloon are connected by the valve core of the chicken intestine; the outlet of the valve core is inside the balloon when the air enters the balloon; the outlet of the valve core is outside the balloon when the air flows out of the balloon; the air pump There is also a branch pipe with a controllable air valve at the inlet, which is used as a pipe for the intake of external air source. 2. The solar energy controllable buoyancy, self-control stable balance helium blue sky spacecraft according to claim 1 is characterized in that: each unit balloon is equipped with an air gas sensor; A cut-off air valve with automatic opening and closing, the opening and closing of the cut-off air valve is controlled by the aircraft automatic control system and driving instructions. 3. The solar controllable buoyancy according to claim 1, the self-control stable helium blue sky spacecraft is characterized in that its structure is made up of a pipe frame and a plate or film skin, and forms three cabins that are connected as one, that is, the balloon cabin , cabin, cockpit, and soft balloons are placed in the balloon cabin; the outer shell of the aircraft has an antistatic coating. 4. The solar controllable buoyancy according to claim 1, the self-control stable helium blue sky spacecraft is characterized in that it is equipped with a propeller propeller fixed on the skeleton shell of the aircraft or an auxiliary structure connected with the skeleton shell of the aircraft.

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