JPH0490997A - Trim control device for high altitude flying aircraft - Google Patents

Abstract

PURPOSE:To move the mass center of an aircraft to a desired position and to provide necessary trim of an aircraft by controlling a moving device for a propellant by means of a mass characteristic managing device, and moving the propellant between a plurality of propellant tanks dispersed in an aircraft body. CONSTITUTION:A space aircraft 10 has the aerodynamic rudder surfaces of a rudder 4a and a body flap 4b. Four propellant tanks 3 are arranged in dis persed position in a fuselage 12, and a propellant for a thruster for controlling orientation is contained in the tank 3. A signal is output from a calculator 1 to each pump 5 and valve 6 according to a command from a mass characteris tic managing part 2, and by operating the pumps and the valves, the propellant is moved through pipings 7a and 7 between the adjoining propellant tanks 3. A mass center G of an aircraft is moved to a pressure center P of the aircraft to provide desired trim. Thereafter, by operating the aerodynamic rudder surfaces of the rudder 4a and the body flap 4b, demand trim is finally realized.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of application] The present invention provides a control system for high-altitude aircraft such as spacecraft that can reduce the demands on aerodynamic control surfaces.
Regarding.

[Conventional technology]

Attitude trim in conventional aircraft is performed using aerodynamic control surfaces (body flaps, elevators, rudders, etc.), and when this method is applied to aircraft such as spacecraft that fly at high altitudes with low dynamic pressure, (control surface area, rudder angle, etc.) may become excessive.

[Problem that the invention seeks to solve]

As described above, in high-altitude flying aircraft such as spacecrafts that fly at high altitudes where dynamic pressure is small, when using normal aerodynamic control surfaces, ICt'i and the demands on the aerodynamic control surfaces may become excessive.

The present invention seeks to solve this problem.

[Means to solve the problem]

A trim control system ftFi for a high-altitude flying aircraft according to the present invention, a plurality of propellant tanks distributed within the fuselage, a propellant transfer device for transferring propellant between the propellant tanks, and a propellant transfer device for transferring the propellant between the propellant tanks, It is equipped with a mass characteristic management device that controls the equipment f.

[Effect]

In the main suction, the mass characteristic control device Kx controls the propellant transfer device f to disperse the propellant within the fuselage and move it between a plurality of propellant tanks. by this,
The center of mass of the aircraft is moved to the desired position and the required aircraft trim is obtained.

As described above, by adjusting the trim by moving the propellant, the demands on the aerodynamic control surface (control surface area, rudder angle), etc. are reduced, its weight is reduced, and the aerodynamic heating of the aerodynamic control surface is reduced. Decrease.

〔Example〕

An embodiment of the present invention will be described with reference to FIGS. 1 and 2.

10 is a space aircraft, which is equipped with an aerodynamic control surface of a f17t-rudder 4a and a body 12 rear end (provided with a friend body 7 lap 4b), which is provided on the parts rising from both shoulders of the main IjL11. 12, four propellant tanks 3 are distributed in the next 1FK, and the propellant for the attitude control thruster is stored in the same tank 3. Each tank 3 has a pipe 7a with pulp 6. Connected and the other 2?l!l
Piping 7&.

-'I) tivC of 7aFi pipe 7 is connected, and the remaining 2
The pipes 7m and 7m are connected to the other end of the pipe 7, and a pump 5 is connected to each of the confluence points of the pipes 7m and 7a and the pipe 7 2a.
There are nine established. Inside xri fuselage 12 [#Fi! Calculator (or dedicated processor) with mass property management N62
The pulp 6 and the pump 5 are controlled by the output signal of the computer 1.

In this embodiment, in response to a command from the mass property management section 2, a computer lFi signal is sent to each pump 5 and each pulp 6 to operate them, thereby allowing the piping 7a, 7
through the propellant tank 3 of four propellant Fi,
The desired trim is obtained by moving the center of mass G of the aircraft relative to the center of pressure P of the aircraft. Thereafter, the rudder 48 and the air control surfaces of the body flaps 4b are operated to finally achieve the required trim.

As described above, in this embodiment, by controlling the amount of propellant in each propellant tank 3, the demands on the aerodynamic control surface (control surface area, rudder angle, etc.) are reduced, and the weight of the propellant is reduced. In addition, the flight range is expanded by improving trim ability and reducing aerodynamic heating on the aerodynamic control surface.

〔Effect of the invention〕

The present invention provides the following effects by adjusting the trim of a high-altitude aircraft by moving propellant between propellant tanks.

(1) Requirements for the aerodynamic control surface are reduced; the area of the control surface and the rudder angle can be reduced, leading to a reduction in the mass of the aircraft.

(2) Since the restriction on aerodynamic heating of the aerodynamic control surface, which is one of the constraints on the possible flight area, can be relaxed, the possible flight area can be expanded.

[Brief explanation of the drawing]

FIG. 1 is an overall view of one embodiment of the present invention, and FIG. 2 is a side view of the same embodiment. 1.-Computer (or dedicated processor), 2.Mass characteristics management section, 3.Propellant tank, 4&-Rudder 4b-.Body flap, 5.Gimp, 6.
...Pulp, 7,7I! I--Piping,
10-・Space aircraft, 11-・Main wing, 12・
... body, G - center of mass, P - center of pressure. 1st Tomoe 7dai: Tube

Claims (1)

[Claims] A plurality of propellant tanks distributed within the fuselage, a propellant transfer device for transferring propellant between the plurality of propellant tanks, and a mass characteristic management device for controlling the transfer device. Features: Trim control device for high-altitude aircraft.